unclassified ad 273106 - dtic · rotary joint, coax-to-waveguide transition and rf cabling are...

UNCLASSIFIED

AD 27"3106

ARMED SERVICES TECHNICAL INFORMATION AGENCYARLINGTON HALL STATIONARLINGTON 12, VIRGINIA

US

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NOTICE: When govexnment or ot-*.,r Irawings, speci-fications or other data irQ it:d for any purposeother than in connection with a definitely related...governmlent 1 ir.=nt o)'eration, the U. S.

Government L incurs no responsibility, nor anyobligation wrhat ;.-ver; Ftnd the fact that the Govern-merit may have for=Latedp furnished, or in any waysupplied the said drawings, specifications, or otherdata is not to be regarded by implication or other-wise as in any manner licensing the holder or anyother person or corporation, or conveying any rightsor permission to manufacture, use or sell anypatented invention that may in any way be relatedthereto.

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Report No. 10075

DEVELOPMlfT OFANTENNA GROUP

OA-1227(XE-1)/TPS

2, June 1957 to 1 May 1961

Contract DA-36-039 SC-74866Dept. of the Army Project3D20-01-001

U.S. Army Signal Research andDevelopment LaboratoryFort Momunouth, New Jersey

HAZELTINE ELECTRONICS DIVISION

HAZiLTINE CORPORATION

LIttle Neck, New York

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HAZELTINE CORPORATION

Report No. 10075

DEVELOPMENT OP

ANTENNA GROUP

OA-1227 (X-I)/TPS

Final Technical Report25 June 1957 to 1 May 1961

Contract DA-36-039 SC-74866Signal Corps Technical Requirements SCL-5296Dept. of the Army Project 3D20-01-001

United States Signal Supply AgencyLaboratory Procurement Support OfficeFort Monmouth, New Jersey

Prepared by

Gerold W. Bugen

and

Paul L. Dominique

Approved: Y

P' 22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONI HAZELTINE CORPORATION

REPORT 1oo75

TABLE OF CONTENTS

Pae

SECTION 1

I PURPOSE 1-1

SECTION 2IABSTRACT 2-I

I SECTION 3

PUBLICATIONS, LECTURES, REPORTS AND CONFERENCES 3-1

SECTION 4

FACTUAL DATA 14-1TASK A ANTENNA GROUP 1

PHASE 1. RF SYSTEM -1Part a. REFLECTOR 4-2

1. General 4-22. Design 4-2

Part b. FEEDHORN 4-5

1. General 4-52. Design

Part c. ROTARY JOINT 4-71. General4-

2. Design4-Part d. COAX-TO-WAVEGUIDE TRANSITION 4-9

1. General 4-92. Design )-9

Part e. RF CABLING 4-91. General 4-9

PHASE 2. CIRCUITRY 4-10Part a. CONTACTOR BOX 4-I0

1. General 4-ic2. Design 4-1i

Part b. ANTENNA CONTROL BOX 4-121. General 122. Design 4-13

Part a. ANTENNA DRIVE MOTOR 4-131. General 4-132. Design 4-13Part d. SYNCHRO ASSEMBLY 4-14

S1. General 4:142. Design 4-14

In

HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

REPORT lOO75

TABLE OF COK79NTS (Cont'd)

Page

SECTICU 4 (Cont'd)

PHASE 2, CIRCUITRYPart s. LUBRICATION :-14

I. General 4-142. Design :1IS

Part f. PRESSURIZATION .- 151. General -152. Design 4-16

Part g. CABLING -16PHASE 3. TESTING -16

Part a. STATIC AND WIND LOAD DEFLECTION TEST -16Part b. SURVIVAL TEST -17Part o, MOISTURE RESISTANCE TESTPart d. TEMPERATURE TESTPart e, VIBRATION TEST -20

PHASE 4. MECHANICAL .-22Part a. ANTENNA PEDESTAL 4-22

1. General 4-222, Design .-22

Part b. TRANSIT CASES -241. General .-24j2. Design •-243. Bounoe and Shook Tests 4-29

Part o. INSTALLATION ACCESSORINS -311. General -312. Design -31

Part d. MISCELLANEOUS -33TASK B SHELTER MODIFICATION -33

PHASE 1. CIRCUITRY .-33Part a. INTERCONNECTING BOX -33

1. General :2. Design R

Part b. CABLING1. General 4-3412, Design -3

PHASE 2. MECHANICAL 4-31. General2. Design 4-3

SECTION 5

CONCLUSIONS 5.11, REFLECTOR AND FEEDHORN 5-12. ROTARY JOINT 5-1

In

P 22 AV 2 R



i REPORT 10075

j TABLE OF CONTENTS (Cont'd)

page

SECTION 6

OVERALL CONCLUSIONS 6-1l SECTION 7

I REC OMMENDATIONS 7-1

SECTION 8

I IDENTIFICATION OF KEY PERSONNEL 8-1

ADDENDUMS

I ADDENDUM A - VOLTAGE STANDING WAVE RATIO MEASUREMENTS AlADDENDUM B - ANTENNA COVERAGE TESTS BI

I ADDENDUM C - ROTARY JOINT HIGH POWER TEST ClADDENDUM D - DESIGN OF OVERSIZED "0" RINGS DlADDENDUM E - ROTARY JOINT, ANTENNA GROUP OA-1227

(•N-i )/TrS ElADDENDUM F - CALCULATION OF HORSEPOWER REQUIRED TO

ROTATE ANTENNA FlADDENDUM G - GEAR CALCULATION G1

I ADDENDUM H - WIND FORCE ON REFLECTOR ASSEMBLY HiADDENDUM I - STATIC LOAD AND DEFLECTION TESTS IiADDENDUM J - MOISTURE RESISTANCE TESTS Ji' ADDENDUM K - TEMPERATURE TESTS KiADDENDUM L - OVERTURNING MOMENT, ANTENNA ERECTION LiADDENDUM M - TESTS ON GROUND ANCHORS M1

I

in

P 2 AM In


REPORT 10O75LIST OF ILLUSTRATICHS

•igure Ti tle page

1. Antenna Group OA-1227(XE-I)/TPS I

2. RF Transmission Paths II

3. Assembled Antenna Reflector III

4. Assembling Antenna Reflector (Sheet 1 of 2) IV

.I Assembling Antenna Reflector (Sheet 2 of 2) V

5. Feedhorn Assembly VI

I 6. Antenna Radiation Patterns (Sheet 1 of 2) VII

6. Antenna Radiation Patterns (Sheet 2 of 2) VIII

17. Rotary Joint Assembly IX

8. Front Panel of Contaotor Box X(Equipment serial nos. 1 and 2)

9. Contactor Box (Equipment serial nos. 1 and 2) XI

I 10. Front Panel of Contaotor Box XII(Equipment serial nos. 3 through 7)

1 II. Contactor Box (Equipment serial nos. 3 through 7) XIII

12. Antenna Control Box XIV

13. Antenna Pedestal XV

14. Control Circuits, Simplified Schematic XVI(Equipment serial nos. I and 2 )

15. Control Circuits, Simplified Schematic XVII(Equipment serial no.. 3 through 7)

16. Synchro System, Simplified Schematic XVIII

17. Lubrication Heating Control Circuita, XIXSimplified Schematic (Equipment serialno.. 1 and 2)

In

P 22 AV '2 R

HAZELTINE ELECTRONICS DIVISIONHAZELTINP CORPORATION

REPORT 10075

LIST OF ILLUSTRATIONS (Cont'd)

Figure Title Page

18. Lubrication Heating Control Circuits, XXSimplified Schematic (Equipment aerial

A nos. 3 through 7)

19. Pressure Control Circuit, Simplified XXII Schematic (Equipment aerial nos. 1 and 2)

20. Pressure Control Circuit, Simplified Schematic XXII(Equipment aerial nos. 3 through 7)

1 21. Interconnection Cabling Diagram XXIII

22. Antenna Reflector Transit Case XXIV

23. Antenna Pedestal Transit Case XXV

24 . Auxiliary "Al Frame XXVI

25. Bumper Jacks XXVII

I 26. Miscellaneous Mounting Components XXVIII

i 27. Lift Sling Configurations XXIX

28. Overall Electrical Schematic Diagram XXX(Equipment aerial nos. 1 and 2)

29. Overall Electrical Schematic Diagram XXXI(Equipment serial nos. 3 through 7)

InP 22 AV 2 A


REPORT 10075 Section 1Page 1 of 78

DEVELOPMRJNT OF (47 text + 31 illustrations)A ANTENNA GROUP and 73 pages for addendumsOA-1227 (XE-I)/TPS A through J

(43 text + 30 illustrations)SECTION 1, PURPOSE

The original purpose of Contract DA-36-039 S0-74866 was thedevelopment of a high power, L-band antenna to provide increasedrange capability and high angle coverage for Radio Set AN/TPS-lD.An IFF channel and provisions for operation with high power radars(up to two megawatts) were to be included.

The equipment to be transportable in two transit cases, eachdesigned to fit on an M-35 truck or equivalent. The transit casesto provide stowage for the antenna reflector sections, feedhornassembly, antenna pedestal, cables, tools and mounting components.

The equipment to be designed in accordance with Signal CorpsTechnical Requirements SCL-5296. Service conditions in accordancewith the specifioaticmnto include operation in high iinds, uniersevere icing conditions and in extremely low temperatures,

Primary power for the antenna drive to be furnished by anexternal, diesel driven engine generator (GFE) delivering three-phase 60-cycle ac power. Synchro reference voltages (11%-volt, 60-cycle and 115-volt, 400-cycle) to be obtained from the associatedradar set.

Initially the contract and specification only covered develop-ment of Antenna Group OA-1227(XE-I)/TPS. The contract and specifi-cation were subsequently amended to provide coverage of antennaoperation with Radar Surveillance Shelter AN/GSS-I.

Development of Antenna Group OA-1227(XE-l)/TPS is covered intask A of this report and the necessary modifications to theshelter in task B. The two tasks were further subdivided into thefollowing phases and parts, details of which will be found inSection #, Factual Data.

TASK A - ANTENNA GROUP

PHASE 1. RP SYSTEM

Part a. ReflectorPart b. FeedhornPart a. Rotary JointPart d. Coax-to-Waveguide

TransitionPart e. RP Cabling

In Page 1-1PI aAV A R

HAZELTINE ELECTRONICS DIVISIONR 1HAZELTINE CORPORATION

REPORT 10O75 Section 1

TASK A - ANTENNA GROUP (Cont'd)

I PHASE 2. CIRCUITRY

Part a. Contaotor BoxPart b. Antenna Control BoxPart o. Antenna Drive MotorPart d. Synobho AssemblyPart e. LubricationPart f. PressurizationPart g. Cabling

PHASE 3. TESTING

PHASE 4. MECHANICAL

I Part a. Antenna PedestalPart b. Transit CasesPart c. Installation AccessoriesPart d. Miscellaneous

I TASK B - SHELTER MODIFICATION

PHASE 1, CIRCUITRY

Part a. Interconnection BoxPart b. Cabling

PHASE 2. MECHANICAL

I

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REPORT 10075 Section 2

SECTION 2. ABSTRACT

The development of Antenna Group OA-1227(XE-I)/TPS (task A)consumed a total time of approximately three years. Developmentof the shelter modification (task B) was much simpler and addedapproximately six months, making a total development time ofapproximately 3-1/2 years.

The first two test models are alike and employ fuses for pro-tection in the three-phase, 60-cycle power lines. To improvereliability and provide simultaneous opening of the three powerlines, the subsequent five test models (serial numbers 3 through7) are provided with a circuit breaker in place of the above fuses.In addition, minor control circuit modifications were effected onthe last five equipments delivered.

The antenna reflector contour and size, is based on an existingfixed station antenna (Antenna OA-1124/FPS). The sectionalizationof the reflector and design of support and feedhorn assemblies(Task A, Phase 1, Parts a. and b.) were subcontracted to the DonaldS. Kennedy Co., Cohasset, Massachusetts.

Design of transit cases was also subcontracted to the DonaldS. Kennedy Co., since the bulk of the items to be stowed (i.e.,reflector sections feedhorn assembly and reflector and feedhornsupport assemblies 5 were being designed by them.

The antenna pedestal was designed by Hazeltine for transporta-bility and to comply with the other specification requirements.

The balance of the components, with the exception of the coax-to-waveguide transition (subcontracted to Diamond Microwave Corp.),were designed by Hazeltine and its subsidiary, Suffolk Products Corp.

Problems encountered in the design of the reflector, feedhorn,rotary joint, coax-to-waveguide transition and rf cabling are dis-cussed in Phase 1 of Task A. Control circuitry problems, for thaantenna group, and their solutions are discussed under Phase 2 ofTask A, and shelter modification circuitry under Phase 1 of Task B.

Problems which were strictly of a mechanical nature, such astransit cases and soil anchors, are discussed in detail In Phase 4of Task A and Phase 2 of Task B.

Page 2-1P 22 AV 2 R



SECTION 3. PUBLICATIONS, LECTURES, REPORTS, CONFERENCES

PUBLICATIONS.

(1) Contract DA-36-039 S0-74866.

(2) Signal Corps Technical Requirements SCL-5296.

(3) Design Plan for Antenna Group OA-1227(XE-l)/TPS,Hazeltine Report no. 5227.

(4) Operating and Performance Tests on Antenna Group0A-1227(XE-I)/TPS, Hazeltine Report no. 5122.

(5) Technical Manual for Antennr *roup OA-1227(XE-I)/TPS.

(6) Supplement to Technical Manual for Antenna GroupOA-1227(XE-1)/TPS.

(7) Revised Coverage for Antenna OA-II24/FPS( ) dated19 September 1956.

(8) Production Teats for Antenna Group OA-1227( )/TPS,Hazeltine Electronics Division Test Procedure 654-A.

(9) Technical Proposal for Design and Construction ofAntenna Group OA-1227( )/TPS,dated 4 January 1957,Report no. 5207.

CONFERENCES.

(1) Evans Signal Laboratory, Belmar, New Jersey, 3 October1957. Attended by Signal Corps and Hazeltine.

Resume

a. Clarification of items in specification.

b. Discussion of design philosophy.

(2) Hazeltine Electronics Division, Little Neck, New York,10 October 1957. Attended by Signal Corps and HaZeltine.

Re sume

a. Interpretation of specification on method of inputto rotary joint.

I

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P22 AV 2R


I REPORT 10075 Section 3

j b. Type of lubricating oil to be used in the pedestal.

(3) D. S. Kennedy & Co., Cohasset, Massachusetts, 23 October1957. Attended by Signal Corps, Hazeltine and Kennedy.

Resume

a. Construction and size of transit oases.

b. Design of feedhorn and support.

c. Erection of the reflector assembly.

d. Calculation of torque requirements.

(4) Hazeltine Electronics Division, Little Neck, New York,21 November 1957. Attended by Signal Corps andHazeltine.

Resume'

a. Method of unloading transit cases from trucks.

b. Erection assembly sequence.

c. Availability of rf cable.(5) Evans Signal Laboratory, Belmar, New Jersey, 9 January

1958. Attended by Signal Corps and Hazeltine.

Re sumre"

a. Discussion of Design Plan for Antenna GroupOA-1227(XE-I)/TPS, Hazeltine Report no. 5122.

b. Amendment of speclfication specifying 1/2 megawatttransmission line to pedestal.

c. Signal Corps intent to change speoification tospecify operation with shelter AN/GSS-1 instead ofAN/TPS-ID ground radar.

(6) Evans Signal Laboratory, Belmar, New Jersey, 22 January1957. Attended by Signal Corps and Hazeltine.

Resumi

a. Presentation of list of exceptions to the specifica-tion, by Hazeltine, due to additional items requiredby the Signsa Corps, prior to approval of the DesignPlan.

In Page 3-2P22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION1 REPORT l007• Section 3

b. Further discussion concerning use of Antenna GroupOA-1227(XE-I)/TPS and shelter ANI/GSS-I.

(7) Hazeltine Electronics Division, Little Nook, New York,27 February 1958. Attended by Signal Corps andHazeltine.

i Resume(

a. Discussion of Design Plan Approval.

b. Limitation on use of M-35 trucks in transporting andunloading of transit cases.

1 (8) Hexagon Building, Fort Monmouth, New Jersey, 13 March1958. Attended by Signal Corps and Hazeltine.

I Resume'

Use of truck M-35 for transporting transit cases.

a. Possible drop test modification due to provisionsfor top lift only.

b. Use of special jacks under front bumper during

unloading to limit strain on front axel.

a. Attachment of "A" frame to front bumper.

(9) Evans Signal Labs, Belmar, New Jersey, 26 March 1958.Attended by Signal Corps and Hazeltine.

Resume'

Requirements for modification of shelter AN/GSS-l foruse with Antenna Group OA-1227(XE-I)/TPS.

(10) D. S. Kennedy Co., Cohasset, Massachusetts, 22 April 1958.Attended by Signal Corps, Hazeltine and Kennedy.

Resumed'

a. Location of pedestal in transit oases.

b. Discussion on various tests to be performed ontransit cases.

c. Method of raising reflector into position.

i

In Page 3-3

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HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATIONA• REPORT l007• Section 3

I (11) Evans Signal Laboratory, Belmar, New Jersey, 29 April1958. Attended by Signal Corps and Haszeltine.

Resume

a. Discussion on Spare parts for Antenna GroupOA-1227(X1V- )/TPS.

b. Discussion on various equipment tests to be per-formed.

c. Specifications for possible lubricating oils weregiven to Hazeltine by Signal Corps.

(12) Signal Corps, Fort Monmouth, New Jersey, 11 and 23June 19*8. Attended by Signal Corps and Haesltine.

I Resume

Request for contract changes one anchoring methods;vibration, drop ad bounce tests; lubricating oil andmodifications for M-35 troeka.

(13) Fort Bliss, Texas, 30 March 1959 through 16 April 1959.Attended by Signal Corps and Nazeltine.

Resume'

Field Evaluations of Antenna Group OA-1227(X3-1)/TPSand shelter AN/GSS-l modification kit.

(14) Evans Signal Laboratory, Belmar, New Jersey, 28 April1959. Attended by Signal Corps and Haseltine.

Re sLWI

a. RI cable difficulties

b. w'±.vory schedules

(15) Port Bliss, Texas, 15 June 19!9 through 18 June 1959.Attended by Signal Corps and Hazeltine.

Re. uuin

a. New rf cable (RG-19A/U) assembly evaluation,

b. Observation of disassembly, erection of AntennaGroup OA-1227(XN-1)/TPS and operational tests.

A

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c. Discussion of mechanical difficulties encountered

during evaluation tests.

d. Target Acquisition data and blip-scan ratio recordings.

(16) Evans Signal Laboratory, Belmar, New Jersey, 7 JulyJ 1959. Attended by Signal Corps and Hazeltine.

Re sam•

Discussion of field evaluation tests at Fort Bliss,Texas.

(17) Fort Monmouth Piocurement Office, Fort Monmouth, NewJersey, 22 September 1959. Attended by Signal Corpsand Hazeltine.

Resume

Discussion of design and contractual problems.

a. Compatability with Radar Set AN/UPS-I.

b. Packaging of running spares, and shelter ANI/SS-Imodification kit.

c. Modification of Antenna Group OA-1227(XE-l)/TPS inaccordance with findings at Fort Bliss, Texas.

d. Addendum to instruction books to reflect modifl-cations.

(18) Fort Monmouth, Fort Monmouth, New Jersey, 27 September1960. Attended by Signal Corps and Hazeltine.

Resume

Review of corrosion on Antenna Group OA-1227(XE-I)/TPS.

I

In Page 3-5P 22 AV 2 R


" REPORT 1007S Section 4

SECTION. L. FACTUAL DATA

INTRODUCTION

As outlined in Section 1, Purpose, this report divides thedevelopment of Antenna Group OA-1227ý'XE..I)/TPS into two tasks;A - Antenna Groupand B.- Modificatioi. of Shelte'r, Task A issubdivided into five phases, with phases -, .nd three beingfurther divided into two parts each and phase two into seven parts.Task B is subdivided into two phases, with phase one being furtherdivided into four parts.

The' following factual data is presented in. the same order asoutlined in Section 1. The overall schematic diagrams (figures28 and 29) are supplied for reference to show the electrical tiesbetween the pedestal and shelter AN/GSS-l. Figure 1 shows AntennaGroup OA-1227(XE-I)/TPS erected and ready for service.

TASK A. ANTENNA GROUPS(See figure L)

Antenna Group OA-1227(XE-l.)/TPS is a high gain transportableantenna system designed for use with Radar Set AN/TPS-lD asinstalled in Radar Surveillance Center AN/GSS-I.

PHASE 1. RF SYSTEM(See figure* 2)

The rf systeta,for the antenna group,transmits and receivesboth search radar and IFF signals. The radar pulses at 1250 to1,350 negacycles, from the AN/TPS-lD receiver;-transmitter units(RT-212/TP -1D) are fed through coaxial cable, to the coax towaveguide transition. Then, through the rotary joint to the feed-horn,

The IFF pulses,at 1020 t 18 megacycles or 1100 t 18 megacyclesare fed from Recelver-Transmitter RT-211/TPX through the shelterInterconnecting box and via coaxial cable to a coaxial connectionon the bottom of the rotary joint. From the top of the rotaryjoint,another coaxial cable feeds the IFF signals to the feedhorncoaxial connection.

Difficulties were encountered in meeting the specificationrequirements for the v oltage standing wave ratio (VSWR),of.l.3 tol,at the input to the rotary joint, and I.5 to I from the outputof Radio Set AN/TPS-ID. The difficulties were overcome by holdingthe coax-to-waveguide transition, rotary joint and feedhorn to verystrict tolerances. The VSWR measurements of the first test modelare provided in addend=n A of this report.

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5 REPORT 10075 Section 4k

Part a. REFLEOTOR

1. General(See' figure 3)

The reflector is approximately 40 feet wide and 11 feet high,and produces a search radar horizontally polarized beam,approxi-mately 1,7 degrees wide and 6.0 degrees high. The reflector hasa parabolic trough-type configuration and produces a cosecantsquared pattern. The IFF beam produced is vertically polarized andapproximately 1.8 degrees wide and 7.5 degrees high. Antenna coveragetests are given in addendum B of this report.

The reflector is constructed in eight sections, designed for

easy assembly and disassembly (see figure 4).

2. Design

The contour and size of the reflector Is based on fixed sta-Lionantenna reflector OA-1124/PPS( ). The primary design considerationwas suitable sectioning of the above reflector and supports,so itcould be quickly erected, and easily stowed in a small volume transitcase,

In order to satisfy the requirements of a quick disconnect fastener,that would support the large fmrces involved, it was necessary todesign a new fastener. A cast fastener of 356-T6 aluminum alloywas designed to support a static load of 20,000 lbs. with no appre-ciable motion. The final configuration arrived at (after testsat Northeastern University, Boston, Massachusetts) is a taperedconnection,with a 200 included angle on the male and female half.The line of force was designed to pass directly through the centerof the contact area. The angle was chosen,as it closely approxi-mated spherical surface at the diameter used and had sufficientfriction to prevent slippage. The final design held together under20P,00 lbs. of tension or compression. This was emphasized duringthe static load test when it was discovered that two connectionswere not secured in the reflector supportat points of maximumstress, after the reflector was fully loaded. (The deflectionsrecorded during static load test showed that the reflector andsupport could withstand about 50% greater wind loadings withoutpermanent set.)

The next problem on the reflector was how to provide astructural dissection that would allow stowing all sections inone transit case. As l4 or even 10 sections presented too greata tooling and attachment problem, eight sections were decided upon.Because of the width available, a thickness of eight inches was

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"HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

MEORT 10075 Section 4

I the maximum depth possible for each section. This depth wouldnot support the load (imposed by the wind and ice loading) ade-quately, so an additional bracing means was devised. A mainhorizontal truss of four sections was provided (of the propersection), and braces were attached by means of rod-end bearings toprovide the necessary pivot arrangement. Four braces were pro-vided for each section. The braces stowed onto the main truss bymeans of brackets and Air-Took 1/4 turn fastener. During assemblyof the sections the cross pin in the. Kennedy designed quickfastener repeatedly came loose. The Spirol pins used were foundunsatisfactory and were replaced by solid pins (Groove).

Tooling presented many problems. In oeder that the reflectortolerance could be held after assembly, it was necessary to makeelaborate welding and machining jigs. All tubing was precut tofinished size prior to welding. The major part of the panelback-up structure was welded. The welded section was transferredto machining jigs, and all convections w ere machined. The sectionwas then transferred to a screening jig and the 5/8 squarex screenattached. The screen is attached to the panel back up structure bytack welding approximately 7 inches on center to all face tubes,and secured to the tube at the perimeter by means of a cap strip,cherry riveted in place over the raw edge. The section was thentransferred to the mold along with adjacent sections, fastenedtogether and final adjustment made to fit the surface of the sectionto the mold surface. After fitting, the remaining welding was doneon the mold. This welding consisted of a seam on tolescopingmembers that were clamped in a predetermined stressed position;so that, when relaxed, the proper surface contour was maintained.The section was then removed and the screen tighteneA to eliminatethe excessive bag between face tubes.

The horizontal truss and braces were assembled and welded on onejig, and machined on another jig.

The assembled reflector was checked for proper alignment by meansof cross wires.

The •,eflector support had to be designed at a great structuraldisadvantage, due to the desired location of the reflector to thepedestal. As it was much too large to be stowed in one piece itwas broken down into five parts, left and right supports, rearsupport, front support and center support. Due to large stresses,the majority of tubes were 3 inch I/4 wall or 3 inch 3/8 wall6061-T6 aluminum alloy. Where castings of 356-T6 aluminum alloywere used, the minimum wall thickness had to be made double thetube wall, due to axial and bending loads. A complete stressanalysis and several models were made to satisfy the requirementsof the loads encountered in each member. As the quick disconnect

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Kennedy fastener did not lend itself to the joints of the support,high strength bolts, and tapered bosses,were used to transmit thebiggest loads. Pivot points with Heim bearings were provided atthe rear of the left and right support to facilitate erection.Welding and machining jigs were used to fabricate all sections.

Two inner and two outer legs (actually trusses) were used toconnect the reflector to the reflector support. They were simplyconstructed in the form of an "N" and attached by means of theKennedy quick connect fastener. A welding and machining jig wasused to fabricate both.

Because of the heavy tube wall thicknesses in the supports andodd joints of tube to tube connections, many special weldingteebniques were required to limit distortion and provide soundwelds.

The Fort Bliss, Texas evaluation tests revealed minor mechanicaltroubles as follows:

(1) The large one inch structural bolts used for assembling'%he reflector supports became clogged during the testsawrl t.ended to bind and cross-thread.

A cleaning groove has been milled across the threads ofthe structural bolts, this allows any dirt on the bolt,or in the mating threaded hole, to roll into the groove;thus avoiding jamming of the threads.

(2) Identification tags were decals secured with glue and felloff during the tests.

The decal tags were changed to metal and are no'- securelyfastened with drive screws.

Inspection of the reflector and support assemblies 'ftei theevaluation tests revealed other minor problems, which -ware cor-rected as follows:

(1) The clevis arms,connecting with the auxiliary "A" framewere extended to prevent the frame from rubbing againstthe lower center reflector panels during erection.

(2) A slot was milled into the clevis to prevent damage tothe "A" frame, if hooked up incorrectly during erection.

(3) Two set screws were added to hold the self aligning bear-ings in their mountings.

(4) Pins in the Kennedy quick disconnect fasteners, used onthe reflector, were changed from groove to straight pinsbrazed in place.


HAZELTINE ELECTRONICS DIVISIONR 10075 HAZELTINE CORPORATION Section 4part b. FEEDHORN

1. General(See figure 5)

I The feedhorn (antenna feed) is a dual polarized horn. Inputs fromthe search radar and 1FF ra'dar are both sections of R6-69/U waveguide,with the search radar input rotated 900 (with respect to the IFF radar

I input) to insure a high degree of isolation. The energy,from eitherchannelenters the flared section of the feedhorn, .propagates to theaperture and. from there illuminates the reflector. The seadich radarenergy'is horizontally polarized and the IFF energy verticallypolarized.

I The dual polarized horn has several advantages over the normal dipolefeed, placed in front of a single polarized feedhorn. (1) Either inputis capable of handling a power level equal to the maximum waveguidepower. (2) The radiated patterns are controlled by the aperture dimen-sions only, and does not affect the other radar feed, a$ do dipolesand reflecting flaps placed in front of the feedhorn mouth. (3) The

I dual polarized horn is simpler in constructioný, than the combined feedsof the horn and dipoles,

The feedhorn and associated waveguide are assembled together tofacilitate stowing and antenna erection. When erected, the feedhornis situated at the focal point of the reflector, uhich concentratesthe energy Into a narrow beam (see antenna patterns in figure.6).

2. Design

The feedhorn presented many problems. The primary problem.was todevelop a horn that would give the electrical characteristics thatwere required by specification. Development from start of design toa final design, took place over a period of one year and four months,approximately. About 1800 hours of work were spent .in developmentand testing prior to shipment of first unit.

A Tchebyscheff feed was originally proposed but did not appeazLi 2itable early in the design. . e major part of the effort was spent

in development of a flared feedhorn with. Radar and !FF connections.For ease of fabrication a sheet metal horn was selected. 'The majordrawback to this type of construction was holding the tolerances, whichwere found necessary after many tests, to ±0.010 inches of the desiredconfiguration. A cast horn could have been used but, by the time afinal design was determined, there was insufficient time to get asuitable casting'with the desired tolerances. All parts of the hornwere machined-to exact size'(0-..003 inches) before welding. 'The edgejoints were machined in a manner so that no indside welding would be..rfeeded,and thereby'require no internal hand finishing. A special hold-Ing fixture was necessary to maintain the desired toleranoe. Manytrials were necessary to obtain the desired matching. Because of theinherent critical design of the-horn-each one must be matched and checkedin free space and finally checked with a reflector on,.an antenna range.

The feedhorn support had to place the horn accurately In place with-out adjustment. The non-adjustable feature placed the feed systemat an extreme disadvantage. Most critical was the vertical angleof inclination to the reflector. Also critical, was thefocus which was finally determined to be 145.6 inches from the

IIn Page 4-5



reflector surface point of origin. In order to keep a maximum areafree of interference from feed supports, and to simplify the feedsupport, the waveguide was used as a structural member of the feedsupport system. In order to gain maximum rigidity and positiveplacement of the hcen,th'ee "A" frames were attached to the horn,and the two lower attached to one point at the bend of the wave-guide run. Another problem was the critical length of thehorizontal run of waveguide. The waveguide. flange had to terminatewithin 0.06 inches of the pedestal waveguide connection. A veryslight error in the bend would cause a large misalignment. Thewaveguide run from the horn to the bend used a cast twist,availablefrom a previous Kennedy job and simplified that transitionconsiderably.

Many electrical tests were necessary to determine the correctplacement of the horn,as the theoretical placement did not give thebest location for all pattern requirements.

Meeting the original IFF vertical beamwidth specificationrequirement of 6.2 t 0.5 degrees presented a major problem. 7hesolution was a complicated feedhbrn employing 10 beam broadeningprobes and four impedance matching irises. This horn produced thehigh edge illumination required for a vertical beamwidth of 6.20,but also produced a ripple of at least 3db in the secondary verticalpattern. Further modifications produced the feedhorn of finaldesign, whinh, while not r-eting the original requirement of 6.2degrees, has .* followl-" advantages:

(1) Increased high angle coverage. - The upper one-half powerangle will "be 6.3 degrees above the horizon, 0.7 degreeincrease In vertical coverage.

(2) -Increased gain. - An IFF gain increase ef at least 1.2dbwas realized.

(3) Lower VSWR. - The IFF VSWR was much improved, enablingmeeting the specification requirements in this respect.

(4) Smoother secondary vertical pattern. - Vertical patternsshow secondary ripples of 1db.

(5) Mechanically simpler. - The new horn is of much simplermechanical construction, therefore easier to produce.

Pointing out the above advantages to the Signal Corps, resultedin a specification requirement change in the IUP vertical beamwidthto 7.8 t 0.5 degrees, and enabled use of the improved feedhorndesign.

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"I HAZELTINE ELECTRONICS DIVISION

HAZELTINE CORPORATIONIREPORT 1OO7~ Section4

Part c. ROTARY JOINT(See figure 7)

1. General

The rotary joint for Antenna Group OA-1227(XE-I)/TPS is pres-surized and transmits the radar and IFF signals from the coax-to-wavegulde transition to ther fpedhorn.

The rotary joint has a waveguide flange input, enabling directconnection to waveguide, for coupling *a high power radar (up to twomegawatts).

The coaxial section of the rotary joint consists of a centerconductor which rotates with respect to the lower waveguide sectionof the joint,and an outer conductor which is divided into an upperand lower section. The two outer conductor sections are connectedby a choke joint,which permits the upper section to rotate. Thelower section is fiXed to the lower wavegulde and the upper sectionto the upper waveguide sections of the rotary joint. The upperwaveguide section consists of a doorknob-type transition which feedsthe rf power from the coaxial section into the upper waveguide. Thelower wavegulde section consists of a similar transition. Matchingirises, in each of the upper and lower waveguide sections, matchthe rotary joint to the waveguide sections and thus minimize reflec-tions withain the rotary joint.

The IFF energy is also coupled to the feedhorn through the rotaryjoint. A center coaxial conductor with slip rings (fingers) permit-ting the rotation. Coax connectors on the upper and lower transistions

1 permit connecting the IFF oables.

In the event the antenna is used with a high power radar (1.5to 2 megawatts) facilities for pressurizing the rotary joint areprovided, with pressure windows located in each of the upper andlower waveguide sectionS. A pressure switch is also provided toindicate normal and subnormal pressures.

2. Desian

The rotary joint is an original Hazeltine design. The door knobupper and lower transitions are basically a scaling of door knobtransitions used in other rotary joints at higher frequencies. Thelocation of the short circuit and elevation of the doorknob werevaried to achieve an optimum transition. A matching iris was thenintroduced In the waveguide to complete the matching of the tran-sition. Location of the several variables was made during low powerVSWR tests. A more ruggedized unit was then fabricated and testedat higher power. No breakdown resulted in this transition during thetest. Refer to addendum C, of this report, for high power test cal-I culations of the rotary joint.

In Page k-7P22 AV 2 R



The IFF channel is also an adaptation of a previous rotaryJoint design. The design employs finger contacts for both theinner and outer conductors of the coaxial line. The major problemwas a misia tch,.resulting In a high VSWR. The HN connectors atboth ends of the channel were found to be the cause of the mismatch.The match of the connectors .was improved by modifying the dimensionsof several of the insulators. The modified connectors lowered theIFF VSWR to within requirements.

Pressurizing the rotary joint presented. by far the largastproblems. The first problem was obtaining pressure windows, atthe required two megawatt rating. The original windows were acommercial product, made by Airtron, Inc., constructed of afiberglas material. When tested under pressure, with two megawattspeak power, the material buckled outward toward the lower pressureside, and subsequent inspection revealed burn marks at points ofmaximum F-field. A new pressure window was designed by Hazeltineusing Ruby Muskavite (mica) material. The new window handled thepressure adequately and showed no evidence of breaking down whensubjected to 2..15 megawatts rf power.

The main pressurization problem was trying to construct therotary joint to meet the specification requirement of a maximumpressure loss of 0.4 psi in 24 hours when subjected to 30 psia.To meet this requirement, oversize "0" rings ksee addendum 1) fordesign) were placed in the pressure window seals. A pressureloss of slightly over one psi per day still occurred. Furthermodifications could have been affected, as follows, to reducethe leakage.

(1) Increasing bellows strength and therefore the sealingpressure. However, there is a maximum limiting surfacepressure at which seal wear life is sacrificed for alittle less pressure. Present design enables the rotaryseal bellows joint to function safely below this level.

(2) The fine finish on the sealing surfaces, could conceivablybe made finer, but a harder closer grained material wouldbe required. A compromise was effected here by using ahigh grade graphite ring, with superior qualities oflong wear and natural lubrication.

Rather than impair the effectiveness of the rotary joint byrequiring design changes in critical areas, Hazeltine discussedwith the Signal Corps the selection of a pressure tank with longerservice life, and a substantial factor of safety for pressure lossThe air tank of final design has a capacity of 386 cubic inchesand a service pressure of 2100 psig. At a pressure loss of over1.6 psi per day the tank provides over 15,000 hours (almost 2 years)of steady life without refilling the tank, thus far exceeding the

1n Page 4-8P 22 AV 2 R



the 5,000 hour reliability specification requirement. On the basisof the above, the Signal Corps waived the specification requirementof a maximum pressure loss of 0.4 psi per day and permitted a lossof 1.35 to 1.675 psi in 24 hours. Refer to addendum E for calcula-tions supporting the pressurization specification change.

part d. COAX-TO-WAVEGUIDE TRANSITTON(See figure 7.)

1. General

The coax-to-waveguide transition is required to couple AntennaGroup OA-1227(XE-I)/TPS to the coaxial cable from the duplexer ofR~dio Set AN/TPS-ID. If the antenna group is used with higherpowered radars (with waveguide output connections) this part will notbe used,

Energy from the coaxial cable is coupled into the waveguide por-tion by a short radiator which is part r~f the coaxial connector.

t 2. Design

The design of the transition is similar to a commercial unit,which was not available at the 600 kw power, required by the speci-fication. The design and production of the transition was subcon-tracted to the Diamond Microwave Corp.

During the electrical tests of the first two units the VSWR wasfound satisfactory, but arcing was heard with less than 500 kw ofpower. It was determined that the m~mt(.•Iifg probe was not makingadequate contact with the wall of £.he wavnguideo Welding the probeto the waveguide was attempted, however, thi.i 4stor.ted the waveguideand was discarded. A threaded probe In the waveguide (and thensoldered) was tried, this provided the detwired contact, but was verydifficult to adjust. The final solution ',ao a probe that wasthreaded into a special seat in the waveguide.

The electrical tests, on the tran.uition of' final design, provedthe VSWR to be satisfactory, with a power handling capacity inexcess of 600 kw.

Part e. RE CABLING

1. General

The rf cabling Interconnects Radar Set AN/TPS=.lD and thecoax-to-waveguide transition. The original design plan was touse Amphenol cable 421-103 to provide the flexibility for storageon the cable reel. However, during evaluation testing the rf cableheated up and power to the antenna was greatly attenuated.

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IP aa AM M R



i To overcome the heating problem, RG-19A/U cable was tried arid foundsatisfactory. However, RG-19A/t cable has a solid core with alarger safe bending radius and other storage facilities had tobe provided.

The original requirement had specified that cables were to be50 feet long. Amending the contract tD have the antenna operatewith shelter AN/GSS-l permitted shortening the cable. Storagefor the shorter cable, with the necessarily large bend radius, wasobtained by clamping to the top inside of the reflector transitcase.

PHASE 2. CIRCUITRY(See figures 28 and 29.)

Circuitry for Antenna Group OA-1227(XE-l)/TPS encompasses thethree phase a-c control circuits, antenna control system, synchrosystem, lubrication and pressure controls, antenna drive motor andcabling to Radar Surveillance Center AN/GSS-l.

Safety switch S108 and interlock switches S101, S802, and S803are provided for personnel safety, removing power from the antennadrive motor when switch S108 or a compartment (i.e., contact or boxS101 or stow look access door S803) is opened or the manual crankS802) Is in its operating position. Interlock switch S804 opensthe antenna drive motor circuit when the antenna is locked in stowposition, to prevent the motor from being accidentally energizedand damaging the equipment. Interlock switches S803 and S101 maybe cheated if visual inspection is required of the components whilethe equipment is in operation.

Part a. CONTACTOR BOX(See figures 8 through 1L)

1. General

The contactor box is mounted externally on the antenna pedestal;it operates and protects the antenna drive motor. The box isremotely controlled from the antenna control box (Part b. below).The contactor boxes supplied with antenna groups serial numbers 1and 2 (see figures 8 and 9) differ from those bearing serialnumbers 3 through 7 (see figures 10 and 11). The two earlier unitsemploy fuses and individual blown fuse indicators, in lieu of thecircuit breaker with one indicator lamp, for protection in thethree-phaa6 power to the antenna drive motor. The above changeand other minor design changes described below, were made to improvethe electrical and mechanical reliability of the equipment. Inaddition, synchro information and the Antenna safety switch areprovided in/on the Contactor Box. See "CONTACTOR BOX" in figures28 and 29 for schematics of the delivered units.

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I 2. Design

The original design of the contactor box was made by Hazeltinein accordance with the specification requirements.

The original design employed an a-c contactor (KI01) and athermal overload relay for the motor.

During the vibration tests (see Hazeltine report 5122, page15) small particles were rubbed off the main contacts by theirholders. The contacts rattled and appeared loose, although theoperation of the contactor was not impaired. However, to improvereliability and to provide a cover over the main contacts, it wasdecided to change the contactor. The new contactor selected is ad-c aircraft type which is vibration resistant, hermetically sealedand lighter than the original contactor.

The new contactor was mounted in its normal operating positionon the vibration table and subjected to the vibration tests. Therewere no mechanical failures during the test and after an electricaltest, following the vibration test, the relay functioned as required,

The addition of the new d-c contactor necessitated adding afull-wave rectifier to the contactor box to convert the a-c to the120 volt d-c required for the contactor coil. The rectifying bridgeconsists of four 1N540 diodes mounted on a component board near thecontactor. The contactor was electrically tested with the recti-fying bridge and found to operate with 65 volts a-c input and dropout with an a-c input of 25 volts. The circuit was operated for25 minutes with an a-c input of 125 volts with no detrimentaleffects to the contactor or diodes.

The original (a-c) contactor had two sets of normally closedauxiliary contacts, and the d-c replacement has but one set. Toprovide control for the ANTENNA ON indicator lamp, in the controlbox, an auxiliary relay (KI02) was added.

The oontactor box as originally designed included a currentsensitive relay to prevent overloading of the motor. However, thisrelay was set to operate at currents much higher than the motorprotection fuses (i.e., 80 amperes for the relay with 30 amperefuses). This would mean that the relay would never operate sincethe fuses would blow first. This was confirmed during the tempera-ture test (see Hazeltine report 5122, page 25) when the fuseswere replaced with steel slugs and the relay never operated. Thethermal overload relay was, therefore, deleted from the contactorbox circuitry.


HAZELTINE ELECTRONICS DIVISIONL HAZELT.NE CORPORATION


Heater relay (M103) failed to operate properly during theenvironmental teats. Even though it was established that thiswas due to a defective relay, it was decided to change to a morereliable type. The new type relay used is hermetically sealedand successfully passed the vibration tests. The new relay islarger than the relay used in the original design and therefore ismounted in a different location, but the accessibility is Impr'ovedand with a tube pin base can be more easily replaced.

The original design of the motor circuit employed fuses (FlOl,P102 and F103) as protection in the three phase line. AntennaGroup OA-1227(XE-l )/TPS serial numbers 1 and 2 were delivered withthis circuitry. To provide more reliable operation and simultaneousopening of all lines to the motor, a three-pole trip free circuitbreaker (OB01) was substituted for the three individual fuses.Replacing the individual blown fuse indicators (DSIOl, DS102 andD 103), a single indicator lamp (DSlOl) was placed across one ofthe three phases. The replacement indicator operates the same asa blown fuse indicator, i.e., illuminates with power applied andthe circuit breaker tripped.

Other minor circuit changes were effected, these are discussedunder the individual Parts as follows:

c. Antenna Drive Motor

e. Lubrication

f. Pressurization

The final design of the contactor box conformedto the specification SCL-5296 and passed all environmental testssuccessfully.

Part b. ANTENNA CONTROL BOX(See figure 123

1. GeneralThe antenna control box is mounted on the wall of Radar Sur-

veillance Shelter AN/GSS-l and provides remote control and monitoringof the antenna operation. ANTENNA DRIVE MOTOR START-STOP switchS201 turns the motor on or off. OIL HEATER switch (S203) controlsheating of the lubricating oil in the oil reservoir. Switch S203operates independently of START-STOP switch S201 in order that theoil may be pre-heated bevore starting antenna operation. Switch8202, mounted behind the front panel, is in the air pressure systemand is normally set to the OFF position when used with the AN/TPS-1D.However, during high power operation (1.5 to 2 megawatts) wherepressurization of the rotary joint is required, the switch is placedto ON, enabling the use of AIR PRESSURE OFF indicator DS204.

P n Page 4-12P flE AVE ft



• i2. Design

The original design of the antenna control box was made byHazeltine to comply with the specification requirements.

The control boxes supplied with the first and secont testmodels cf Antenna Group OA-1227(XE-I)/TPS 'Serial numbers 1 and 2)were manufactured in accordance with the zi.Lginal design. Thecontactor box (Part a) modifications made on serial numbers 3through 7 necessitated minor lamp rewiring of the control box.

In the original design (and serial numbers I and 2) the START-STOP control for the contactor was provided by breaking the neutrallead of the three phase ac. To comply with good design practice,control of the contactor is now provided by breaking one of thethree phases.

Schematic diagrams of the delivered models can be found under"ANTENNA CONTROL" in figures 28 and 29.

Part c. ANTENNA DRIVE MOTOR(See figure 11)

j 1. General

The antenna drive motor is mounted beneath the pedestal anddrives the antenna in azimuth, through suitable gearing, at arotation rate of six rpm in a clockwise direction only. The motoris rated at 7.5 hp and requires an input of 120/208 volts, 60cycle - 3 phase a-c. The motor used is a commercial type with astandard NEMA mounting. To lighten the overall weight of theequipment, Hazeltine requested that the motor manufacturer providethe motor in an aluminum frame.

The motor control circuitry was modified after two test modelsof Antenna Group OA-1227(XE-I)/TPS were delivered. Simplifiedschematic diagrams for each model are shown in figures 14 and 15.

2. Design

The size of the antenna drive motor and design of motor controlc ircuitry were made by Hazeltine in accordance with the specificationrequirements.

To compute the size of motore required, the weight of the reflec-tor and feedhorn were considered with the extreme environmentaloperating conditions indicated in the specification. The.7.5 hpmotor decided upon, proved more than satisfactory under all conditions.Addendum F', of this report, provides calculations supporting thechoice of a 7.5 hp motor.




The design changes in the motor control circuitry, i.e. circuitbreaker replacing fuses are discussed under Part a. CONTACTOR BOXabove,

Part d. SYNCHRO ASSEMBLY(See figure 16I

1, General

The synchro assembly consists of a 5G, 60-cycle synchro trans-mitter (B501) which provides one-speed azimuth information, and a3lTx4, 400-cycle synchro transmitter (B502) which provides 24-speedazimuth information. The antenna drive is geared 1:1 with the60-cycle synchro, and 1:24 with the 400-cycle synchro. Refer toaddendum G for calculations on gearing. A cam driven switch (S501)actuates relay K104 to provide a 400-cycle zeroing voltage to the400-cycle 24-speed synchro motor (B602) in Azimuth-Range IndicetorIP-141/TPS-1D, until the antenna reaches zero azimuth. The 60 and400-cycle synchro reference voltages and the 27-volt do for relayK1014 are taken from Power Supply PP-674/TPS-1D. The 60-cycle one--speed azimuth information in supplied to terminals in Power SupplyPP-674/TPS-ID for use with a PPI repeater.

2. Design

Design of the synchro assembly as made by Hazeltine in accor-dance with the specification requirements. The original designmet all requirements and no changes were necessary.

Part e. LUBRICATION(See figures 17 and I8N

1. 2}eneral

Te antenna drive gear train is force-lubricated by means ofan oil pump geared to the antenna drive.

An oil flow switch (5301) is provided to interrupt power tocontactor Kl01, thus stopping the antenna, if oil flow is missingfor two minutes or more. If flow switch 8301 is closed, OIL FLOW-LOW indicating lamp on the antenna control box is illuminated.When 8301 switch opens, with normal oil flow, OIL FLOW-NORMALindicator lights. Should 8301 fall to open within 2 minutes, thermalrelay K105 will open; breaking the circuit to the bridge rectifiers(supplying the coll of contactor K1O1) thus removing power from theantenna drive motor.

Turning OIL HEATER switch S203 in the antenna control box tothe ON position will provide heating of the oil in the oil reservoirif the oil temperature drops below 12.20C (+100F). Antenna control!

ln 4-14P 22AV2RR



indicator OIL TEMP-NORMAl, will light if the temperature of the oilis about -27.3 0 c (-10 0F) and be extinguished below this temperature,thus providing an indication that pre-heating of the oil is re-j quired, before starting the antenna drivd motor.

2. Design

I The oil heating system as originally designed by Hazeltineessentially conformed to 1he system contained in the first twoantenna groups delivered see figure 17) except that the inclusionof a heating element on the oil feed line was planned for in theoriginal design.

Difficulties encountered in Installing the circular heatingelement in the prototype model indicated the inclusion of theelement would not be feasible for production. Calculationsindicated the element was not necessary and it was decided to omitthe oil line heater pending results of the environmental tests.The single heater in the oil reservoir proved more than adequateat -65oF, and the oil line heating element was deleted from the5design plan.

The original design plan was for an oil conforming to specifi-cation MIL-L-7808 for lubrication of the drive system. Exceptionto this particular oil wqs taken by the buyer (Signal Corps) asit is not readily availabl.e in the field. Hazeltine tried toaccommodate the Signal Corps and investigated all oils, readilyavailable to Signal Cors maintenance personnel. The Investigationproved that all available oils were not suitable for this applica-tion and reversion to the MIL-L-7808 oil was necessary.

Minor modifications in the oil heatin& control circuits wereinstituted In Antenna Group OA-1227(XE-1) TPS serial numbers 3through ; a simplified sohematic of this circuit is given infigure 1;.

Part f. PRESSURIZATIONI (See figures 19 and 20.)

1. General

I Pressurization of the rotary joint for use with high (1.5 to2 megawatts) power is a design requirement in accordance with thespecification. RF and mechanical difficulties experienced meetingthis requirement are discussed under rotary joint. Task A, Phase1, Part c. and mechanical phase 4 respectively. AIR PRESSURE ON andOFF indicators (DS205 and D8204), energized by air pressure switch3805 in the rotary joint, pressure line, are provided as indicationsof correct air pressure. At pressures below 12 lbs. per square inch,

Iln Page. 14-15P 2 AV 2 R



OFF indicator DS204 Is illuminatediindicating below normal airpressure. Pressures above 13 lbs. per square inch actuate switchS805, which illuminate ON indicator DS205, indicating that therotary joint is correctly pressurized.

Antenna Group OA-1227(XE-I)/TPS is primarily designed tooperate with Radar Set AN/TPS-ID at comparatively low (0.5 mega-watt) power, which does not require pressurization of the rotaryjoint. Switch S202 (mounted behind the front panel of the antennacontrol box) is provided to disconnect OFF indicator DS204 whenoperating with low power, to avoid presenting a false impression ofincorrect operation.

2. DesignHazeltine's original design plan for the pressurization control

system proved to be quite satisfactory. However, to simplify thewiring, minor circuit changes were effected after delivery ofAntenna Group OA-1227(XE-I/TPS. Simplified schematics (figures19 and 20) indicate the control circuit changes between the earlierequipments and serial numbers 3 through 7.

Part g. CABLING(See figure 21.)

Cabling for Antenna Group OA-1227(XE-l)/TPS is completelydifferent than that shown in the original design plan. The changeswere necessitated by the contract change calling for operation ofthe antenna group with Radar Surveillance Shelter AN/GSS-1.

All cables except the one to the engine generator were shortenedfrom the original 50 feet specified, since the antenna would belocated about 15 feet from the shelter.

All cabling to the shelter was terminated by connectors tofacilitate quick assembly and disassembly. Additional cables insidethe shelter were required to complete the connections to the unitsfrom the interconnecting box.

The Interconnecting box is discussed under Task B, Phase I.RF cabling difficulties and design changes are discussed in TaskA, Phase 1, Part e.

PHASE 3. TESTING

Part a. STATIC AND WIND LOAD DEFLECTION TEST

The reflector assembly is required to withstand, without damageor impaired performance, the loading effects of wind conditions asdescribed in paragraphs 3.7.1(e) and 4.3.10 of the Technical Require-

,In Page 4-16P 22 AV 2 R



ments SCL-5296. The tests were performed by D.S. Kennedy & Co.at their Hingham Plant on November 12-13, 1958, using a preproduc-tion model of the OA-1227(XE-l)/TPS forty-foot antenna.

Whereas the maximum loading under thn comditions described inthe Technical Requirements is 12.. lbs/sq. ft. (see calculationsin addendum H), the reflector was loaded up to 15.9 lbs/sq. ft.during the tests. No unusual deflections were recorded during the

test, and no appreciable permanent set was measured at its conclu-sion. Radiation pattern tests were conducted before and after thedeflection test. No pattern changes were brought about by thedeflection of the reflector assembly, Thus, on the basis of thesetest results, the antenna is considered to have easily surpassedits technical requirements. The procedures, conditions and resultsof this test are provided in addendum I.

Part b. SURVIVAL TEST

For this test the pedestal was fully erected on its legs withground anchors and tie rods in place, and the reflector assemblymounted upon it. Using an M-35 truck winch and an "A" frame, astatic load was applied to the back of the reflector. The 5500pound load, equal to the maximum survival wind loading, wasmeasured by a 10,000 pound dynamometer.

The results of this test were positive. The entirA structureremained stable, with no damage sustained by any of the structuralmembers. A comparison of radiation pattern tests conducted beforeand after the survival test revealed no pattern changes. A visualinspection of the entire structure, made immediately after thesurvival test, disclosed that the pedestal was inclined 0* 43'from the vertical due to settling of the ground plates, and therewere slight deflections in the ground anchor rods. The antennaassembly is considered to have successfully met its specified re-quirements in this area.

Part c. MOISTURE RESISTANCE TEST

The moisture resistance test was performed in the temperaturealtitude humidity chamber of the Burgoyne Test Laboratory Inc.,Westbury, N. Y. in the presence of USASRDL personnel. A 1600 lb.load was attached to the rotating portion of the pedestal, suchthat the dynamic effects of the reflector assembly would be simu-lated within the confines of the test chamber. The equipment wasthen subjected to a 48 hour initial conditioning test followed bya variable temperature cycle of 48 hours duration, the latterbeing repeated 5 times, The equipment was non-operating exceptfor 15 minute test periods during which measurements were taken,all within 5 minutes after the power was applied.

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During each of the 5 cycles, readings of the operating voltageand current, starting current, and the power of each of the threephases were recorded. Thermocouples, placed at nine separate loca-tions within the pedestal, monitored its temperature conditions.This test was conducted in accordance with the conditions and pro-cedures set forth in paragraph 4.3.7 of Signal Corps TechnicalRequirements No. SCL-5296, 8 May 1956. The procedures followed andthe entabulated results are given in addendum JT.

It was observed that throughout each cycle, both the electricaland temperature readings remained consistent by within ± 10% of theinitial conditions. In all oases, starting time was instantaneous,the pedestal speed remaining constant at 6.2 RPM.

No defects of any nature were observed. Since the performanceof the equipment was not adversely affected during test conditions,it is concluded that the equipment qualifies under this section ofthe Signal Corps technical requirements.

Pprt d. TEMPERATURE TEST

The temperature test was performed in the same location as themoisture resistance test (part c) and conducted in accordance withparagraph 4.3.6 of the Technical Requirements. The procedures,conditions and results of the test are shown in addendum K.

During the cold temperature test certain malfunctions wereobserved. The reasons for these malfunctions were determinedand corrective measures taken as follows:

(1) Malfunction

Initial failure of the pedestal to rotate at -65 0 F.

Reason

From observations made during the test, and subsequentconversation with the motor manufacturer, it is know thatmoisture probably entered the motor case through thenormal breathing process during the 10 day moistureresistance test. It is believed that this moisture froze,thereby locking the rotor. In all probability, highcurrent surges evePaiually melted the ice, whereupon thepedestal began to _'iwction in a normal manner. Had thetemperature test oeen performed prior to the moisture test,this situation would probably not have occurred.

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j Solution

Following the recommendation of the motor manufacturera note will be included in the maintenance manual thatthe motor drain plug be removed and any moisture presentbe allowed to drain out before shipment of the equipment

to a frigid environment.

(2) Malfunction

Almost instantaneous blowing of fuses at looked roto'rcondition.

Reason

Poor choice of fuses.

i Solution

Improper fuses have been replaced with Military Standard90085-70 fuses. These are slow-blow fuses with a minimumdelay time of 6 seconds for looked rotor conditions.This will aid in starting the motor should it ever inad-vertently freeze again. Assurances have been receivedfrom the motor manufacturer that 6 seconds of lookedrotor current will not damage the motor in any way.(Note: at -65°F a 30 second delay is harmless.)

(3) Malfunction

Heater relay failed to close.

Reason

Failure of the particular relay used during the test.Temperature is not believed to be a factor.

J Solution

A second relay has been tested at -65 0°P and found tofunction satisfactorily. This relay has been substitutedfor the defective one.

(4) Malfunction

Motor control thermostat prevented pedestal from rotatingonce it started.

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P HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

*I REPORT 10075 Section 1

Reason

As the pedestal started to rotate the oil began to oir-culate and cold oil came into contact with the thermostatthereby opening it and shutting the motor off, A checkof the thermostat after the test showed it to be set at+20.30F instead of -10oF as called for.

Solution

Thermostat S303 will be set to -100F and will be usedfor the sole purpose of operating a green light on thecontrol panel. This light will be off until the oiltemperature reaches -10 0F. Above -l0OF the light will beon and all oil will be filtered. The Heater ControlThermostat will be set so as toturn on the heater whenthe temperature falls below +100F.

(5) With the above modifications, and the observations madeduring the cold temperature test, it Is felt that thepedestal can be operated instantaneously, if need be,at any of the envý_onmental conditions specified inSCL-5296, thereby bettering the requirements specified

in paragraph 3.7.7.

Part e. VIBRATION TEST

In accordance with paragraph 4.3.1 of the Technical Require-ments, the pedestal subassemblies containing sensitive electricaland mechanical components were subjected to vibration testing.

The tests described below were pe'formed on a vibration tablelocated in the test laboratory of Hazeltine Electronics Division,Little Neck, New York. These tests were witnessed by V. Tristan,a resident Naval Inspector.

(1) Control Box

The control box cover was removed and attached to thoback of the control box. The box was then mounted bymeans of four 1/A - 20 screws to a I" aluminum plate.This plate was then fastened to a 150 lb. 1/2" thicksteel plate which was in turn bolted to a vibration table,

The equipment was vibrated at 1/64." amplltude in threeplanes at frequencies of 5 to 55 cycles/second changingat a rate of 1 cycle/second. The equipment was cycled4 times. A strobe light as well as visual inspection wasused to determine any mechanical resonances, none werenoted. The unit passed satisfactorily.

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P 22 AV 2 R



(2) Synohro Assembly

The synohro assembly was mounted to a fixture which wasbolted directly to the vibration table. Test conditionswere the same as described in paragraph(g, There wereno mechanical resonances noted. The assembly passedsatisfactorily.

(3) Contactor

The contactor was fastened to a 1" thick aluminum plateand vibrated on two separate occasions. The first wasunder the conditions described in paragraph (1). Loose

I washers and other parts rattled during this test due tothe floating contacts but no damage was visible.

The s~cond vibration test was performed at an amplitudeof 1/16" and a frequency of 55 cycles/second for a dura-tion of 15 minutes in each plane. No damage was notedoutside of some particles which were rubbed off the con-

I tacts by their holders.

(4) Contactor Box

I The contactor box was mounted on a 1" aluminum plate. Theplate was bolted to the vibration platform and held approxi-mately 7/8" above it to allow the cable conduit to clear.Test conditions were the same as described in paragraph(lW.The loose contactor parts rattled and the core of thethermal relay moved in and out. There was no damage notedI after the test.

!1II

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PHASE 4. MECHANICAL

Mechanical design problems encountered during development ofAntenna Group OA-1227(XE-I)/TPS are discussed in parts as outlinedin Section 1.

The mechanical design changes for the rf components (reflector,feedhorn, rotary joint and coax-to-waveguide transition) are dis-cussed in Task A, Phase 1.

jDetailed final assign procedures for antenna assembly, dis-assembly and coxrponeint stowage in transit cases are given in theTechnical Manual for Antenna Group OA-1227(XE-1)/TPS.

I Calculations providing the overturn moment, of the assembly,during erection are given in addendum L.Part a. ANTENNA PEDESTAL

(See figure 13)

1. General

Mechanical design of the antenna pedestal was generated tofulfill the electrical, mechanical and environmental requirementsof the equipment specification. The Design Plan was used as aguide for development of the Pedestal.

2. Design

The original design plan of the antenna pedestal componentparts is the same as the final design except as given below.

(a) ANTENNA DRIVE MOTOR. - Lightened by use of cast aluminumframe instead of cast iron.

(b) CONTACTOR BOX. - Component locations were rearranged toaccommodate inclusion of circuit breaker in place of fuses.(Serial numbers 3 through 7 only.)

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SREPORT 10075 Section 4

(c) REFLECTOR SUPPORT. - The lifting points on the originallydesigned pedestal required one short and two long legs of thesling for lifting. To avoid possible mistakes in attaching theslingithe lifting points were relocated to use a sling with threeshort legs.

I (d) PEDESTAL WEIGHT

Before any official drawings existed, a preliminaryestimate was made, predicting the pedestal weight to be approxi-mately 1500 pounds. With later developments and the availabilityof more accurate information, the necessity for a reappralial ofthis estimate was recognized. Listed below are areas where such

I information Influenced this evolution"

(1) Hardware and Internal Components

I Little was known of the weights and quantities ofhardware and components which were eventually in-corporated in the final design.

1 (2) Rotary Joint

All of the electrical and mechanical requirementsof the rotary joint were not known in sufficientdetail to accurately predict its weight. It even-tually proved necessary to employ heavy-wall brassin its construction in order to provide the idealelectrical properties and sufficient strength tocontain the required pressure. Consequently, itsfinal weigth was over four times as great as theoriginal estimate.

1 (3) Main Bearing

The original estimate of the weight of the mainbearing was evolved from ot~hae information of apreliminary nature. It was later found that theweight of the reflector assembly was higher than thepreliminary figure, and that its center of graVitywas further from the center of the pedestal thanoriginally assumed. Thus the offset load momentwas much higher than anticipated. This, in turnnecessitated an increase in the load-carrying capacityof the main bearing with a resultant increase in itssize, and therefore, its weight.

(4) Castings

(a) The wall thicknesses of certain portions of thecastings, such as strength webs and stiffeners,became greater as dictated by optimum foundry

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practices. The relationship between adjacent moltenmasses of various sizes cooling In a moldjmust besuch that distortion is held to a minimum,

(b) Solid cores were used in making the sand molds forthe castings. In removing the cores from the molds,it was necessary to "rap" them in order to work themfree. This "rapping" caused the mold cavities tobecMue slightly enlarged, with the consequence that ageater amount of molten metal flowed into each mold.I result was heavier castings.

The circumstances listed above had the cumulative effectof increasing the pedestal weight to approximately 2600 pounds.

Part b. TRANSIT CASES(See figures 21 and 22.)

1. General

Two transit cases for transport stowage of the antenna groupcomponents are provided. In accordance with the revised specifi-cation requirements, the maximum height of the loaded truck cannot exceed 11 feet and the case's center of gravity shall be low.To comply with these requirements required considerable changesfrom the original design plan (Hazeltine Report No. 5227).

I The antenna reflector case of final design is 146 inches longx 80 Inches high x 86-1/2 inches wide. The antenna pedestal caseof final design is 146 inches long x 81 inches high x 86-1/2 incheswide.

2. DoesIagnAfter the design of the reflector was established, the reflector

transit case design was started. Preliminary layouts showed t*atonly two possible arrangements of the reflector sections could beused to fit the eight sections in one case. Assembly sequence wasconsidered but could not be maintained.

As two connections on each horizontal joint of the section wereavailable the opposite half of the connection was secured to two4 x 4 beams 'in the transit oase bottom for the main support. Thetop side of each section was held by two light aluminum braces,which at first were rubber mounted, but were later revised to a solidmount because of excessive transmissibility during the package test.As the reflector sections used up about 85% of the available spacein one transit case, only a limited number of additional parts couldbe stowed with it. The auxiliary "A" frame, used for erection, wasstowed on the outside as there was no room in either case. As theSignal Corps wanted to unload the reflector case on the truck, aswing out step was provided in front. The tail gate could be usedas a step in the rear. It was not possible to get between the caseand the reflector sections. Access to the reflector sections wasby means of three hinged gates secured by the Kennedy designed con-

In nector (see Phase 1, Part a). Page 4-24P21 AV 2 R



The pedestal transit case presented many more difficult stow-ing problems than the reflector case. Most parts were of a shapethat would not allow econoiiical placement. Most difficult werethe pedestal, pedestal support legs, feedhorn assembly, and centerreflector support. The great majority of parts were of tubularsections, so a clamp was devised using a 1/4 turn Air-Loc fastenerforeclosure. As the clamp had to clamp tightly, the Air-Loc fastenerwas found unsuitable as it could not pull the hinged clamp tightenough. In place of this fastener a Simmons Link Lock #2 was usedwith good results. As the pedestal weighed over 2500 lbs. it pre-sented a large problem in itself. The case could not be made strongenough to take 10G shocks for three hours on an item of this weight,without some attenuation of the shock. Twelve (12) Lord compres-sion mounts that allowed I" of motion were mounted on a 3-1/2"aluminum tube at the six main leg mounting points. As these werecalculated to be on a plane in line with the center of gravity ofthe pedestal, there should be a little rocking motion caused byvibration and shocks, During the package test it was noted thatthere was some rocking, indicating the mounting was not exactlyon the plane of the center of gravity. However, the shock-mounts,pedestal and case showed no signs of damage. In order that the•edestal could be removed first, a gate in the top of the caseover the pedestal) was provided.

Many of the problems that occurred were not apparent duringthe initial proposal. Solution of the problems was arrived atonly after many times the allotted hours. Because of the urgencyof delivery, design of the pedestal transit case suffered greatly.Final design was accomplished only after one was built. As amatter of fact, final placement of the stowed parts was" arrived atonly by actual placement of the full size pieces, and engineeringpersonnel providing on the spot supervision.

In spite of the many difficulties,a sound adequate design wasobtained and few changes would be necessary to optimize the parts.In general the overall design of both transit cases was accomplishedmaintaining a complete structure at all sides.

At various stages in the development and testing of this equip-ment, difficulties have arisen in the fastening of rubber chafingpads to the inner surfaces of clamps on the transit cases. Somerubber pads, seemingly securely attached, could be lifted andpeeled off by hand. Others would vibrate free during a test, andstill others would fall off by themselves, after having beensecurely attached for a considerable period. Continuous investi-gations and testing were condw ted until the causes and remediesfor this problem were discovered.

Among the causes for this deficiency are the following:

(1) Certain adhegives recormaended for bonding rubber to metalsurfaces, although showing excellent strength in tension,

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P 22 AV 2 R Page 4-25


j rPORT 10075 Section 4

proved to be weak in shear. As a result, there waslittle resistance to scuffing and peeling, the mostoomon disturbances to which the pads are exposed.

(2) Some of the rubber samples tested exhibited a relativelyhigh wax content. The presence of wax has a retardantaffect on adhesive bonding.

1(3) Unclean surfaces:

* (a) It was found that dirt, grime or paint were present, under some of the pads which had a bonding deficiency.

(b) The rubber itself has molding powder on its surfaces.I This powder acts as a retardant to adhesive bonding.

(4) Improper application:

I(a) In some eases, it was evident that an insufficientamount of adhesive had been applied, parts of therubber pad surface being without adhesive.

(b) Certain adhesives used~required intermittent stagesof application and air-curing prior to final contact.Doubt exists that these procedures were strictlyfollowed in all oases.

(c) Some adhesives required the application of pressureafter contact. In some instances this may not havebeen done for the required period.

Accidental mechanical abrasion accounted for some of thedeficiencies. There is no adhesive known that can withstandabrasive forces in the magnitude possible during the handling

1 of heavy equipment.

The eventual solution to this problem lay in the eliminationof all of the above factors, which alone, are causes of adhesivebonding deficiencies. This was accomplished by:

(1) Using Eastman 9-10 adhesive, which has a relatively highshear strength, and presents no particular problems inapplication or curing.

r (2) Thorough cleaning of all surfaces.

(a) Metal surfaces cleaned by scraping to bare metal,removing all paint, grime, and oxide films.Metallic dust is wiped off and the surface treatedwith MEK solution.

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I HAZELTINE ELECTRONICS DIVISION

REPORT10075HAZELTINE CORPORATIONSeto4

(b) Rubber surfaces to be cemented are prepared byabrading.

(o) Molding dust is removed from rubber surface bybrushing with MEC solution,

(3) Application of adhesive is administered carefully, soentire pad surface Is covered.

(14) Pressure applied to the rubber pads by closing'the clampI tightly about a pipe.

(5) Rubber having a lower wax content was used, samples beingtested intermittently,

In view of the findings determined by the field evaluationtests and Hazeltine inspection on their return from Fort Bliss,

Texas, the following minor changes were made:

(a) To both transit cases:(1) The bottom portions of both ends were reinforced toI make the case capable of being fork lifted.

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P22 AV. 2 R

HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATIONREPORT 10075 Section 4

I (2) Jam nuts were added to turnbuckles on hold downcables.

I(3) Holes In the case skids were enlarged so they couldaccept the no. 30 hook supplied with the M-35 truck.

(4) All door holding catches were changed to the quickdisconnect type used on the antenna reflector.

(5) All Airlock Fasteners were replaced by a SimmonsLink-Look type fastener.

I (b) To the antenna reflector case:

(1) Clamps were added to the auxiliary "A" frame stowageto prevent end movement.

1 (2) The top member of the door side of the case wasstrengthened.

I (a) To the antenna pedestal case:

(1) Brackets were added on the top of the tool box toI secure the antenna control box during transit.

(2) A reinforcing gusset was added to the upright nearI the tool box.

(3) The access door in the top was redesigned toeliminate brackets protruding in the pedestal nrea.

(4) Brackets that support the bridges were set furtherapart to provide more room in the contactor boxarea. The resultant long bridges were reinforcedto prevent bending.

(5) Lifting holes were reinforced.

(6) The method of securing the cable reel was changedfrom "J" bolts to a clamp through the center hub.

(7) The rear access door was reinforced.

(8) The lead of pedestal bridges were chamfered tofacilitate loading.

(9) Bracket stops were added to prevent the Jack screws,on the tripod legs, from unscrewing during transit.


IHAZELTINE ELECTRONICS DIVISION

HAZ9LTINE CORPORATION


(10) Tha antenna rear support stowage was redesigned; froma stud that fastened to the threaded hole in the support)to a socket type mount.

(11) The stowage of the front antenna support was relocatedto prevent the captive screws from rubbing on the leftinner truss,

3p Bounce and Shook Tests

5 The transit eases were subjected to bounce and shook tests inaccordance with the provisions of 'paragraphs 3.8 and 4.3.of theTechnical Requirements No. SOL-5296, These teats were conductedfor Hazeltine Electronics Division under the directionfor asetin ElctroicsDivsio undr te drecionof USASRDLpersonnel for the purpose of qualifying the transit case as ashipping container for military radar equipment.

(a) BOME TEST

Each transit case, with contents in place, was mountedon a 4600 pound steel structure simulating a truck.bed. Thetransit oases were secured to the carriage with four chains equippedwith load binders and restricted from lateral motion by cornerfenced attached to the carriage. At Package Research LAborator-.Rookaway, New Jersey, the carriage was placed upon the vibratimgplatform of an L.A.B. Corp. package tester of 10,000 lbs. chpsaity,f" amplitude, operating in a synohronous'ciroular orbit In the

vertical plane. Vertical forces were measured by an accelerometeraffixed to the carriage, its amplified output being displayed on a

CRT oscilloscope. The results of the test are as follows:

(1) Reflector Case

$ One guy rod clamp slipped allowing the free end towhip against parts below. The test was interruptedand it was seen that improper tightening of clampbolts allowed this to occur. After the clamp wasrelocated and tightened, no further looseningoccurred.

The top "A" frame clamp brokeadjacent to the weldwhich attached it to the case. The test was inter-rupted and it was found that a rubber liner in theclamp had been lost, and the "A" frame cable wascausing abrasion to the "A" frame. Several changeswere made on the reflector case and the "A" frame asas ziesult of this test. A clamp was used to replacethe yoke which held the apex of the "A" frame tothe transit case. The upper swiveling guide of the "A"frame was made secure with a fastener and a storagebin was installed on the "A" frame for stowing the"A" frame bridle.

In Page 4-29P22 AV 2 R



An anchor bolt sheared at the frame end of the rearstabilizing tube. The test was interrupted, and thebolt replaced. The bolt was probably faulty since allother anchor bolts held. Peaks of lOg and 7g weresubsequently reachud without further failure.

(2) Pedestal Case

After peaks up to log, a clamp attached to the pedestalmount, holding the "Right Inner Truss" broke near theattachment weld. The test was not interrupted.

After 30 minutes of testing, it became evident that theconcentration of the pedestal weight at one end of thecase caused an imbalance, leading to higher values ofvertical acceleration than would normally be encountered,The test was interrupted and 150 pounds of iron addedto the end of the carriage opposite the edestal. The150 pound weight was later increased to 36 pounds.

A captive pin backed outreleasing one of the levelingJack screws. The test was interrupted, and the Jackscrew was removed and left out for the remainder ofthe test. A positive locking device was used to re-place. the captivating pin for the jack screws.

All other broken clamps were repaired, reinforced andrelocated so as to prevent further failure.

(•) Conclusion

After these minor failures had been discovered andcorrected, the tests proceeded without further diffi-culty. The transit cases were considered suitable fortheir intended purpose in cognizance of paragraphs3.8 ard 4.3 of the Technical Requirements. A completedescription of the tests and recorded data is includedin Section F of Hazeltine Report No. 5122 "Operatingand Performance Tests."

(b) SHOCK TEST

In accordance with paragraph 4.3.5 of the Technical Require-ments, both transit cases were subjected to a free fall drop testl

Each case was supported at one corner of its base by a block5 inches in height. A 12-inch block was placed under the othercorner on the same end of the transit case. By means of a quick-release hook, the opposite end of the case was raised 6 inches andallowed to fall freely. This operation was repeated until each of,the four corners had been dropped.

In Page 4-30

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* I HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

I REPORT 10075 Section 4

I (1) Reflector Case

The reflector case was tested at the Package ResearchLaboratory, Rockaway, New Jersey. An inspection re-vealed no damage as a result of this test.

1 (2) Pedestal Case

The pedestal case was tested at Suffolk Products Corp.,Greenlawn, New York, with no damage resulting fromthis test.

A description of the shock tests is included as sectionH of Hazeltine Report No. 5122, "Operating and PerformanceTests.1"

Part c. INSTALLATION ACCESSORIES(See figures 24 through 27.)

1. General

In accordance with the contract requirements accessory componentsare included, to aid in the assembly of Antenna Group 0A-l227(XE-l)/TMS.The contract was modified to include the truck bumwper support jacks(figure 25), when investigation determined that the front axle ofthe M-35 truck was only rated for an additional 500 lb. load.

2. Design

The auxiliary "A" frame as originally designed was thought tobe foolproof. However, during the field evaluation tests at FortBliss, Texas, a tearing of the frame occurred during erection ofthe antenna. Hazeltine engineers examined the damaged frame andconcluded the failure had occurred because the erection instruc-tions had not been followed. However, in order to prevent othersuch occurrences, Hazeltine redesigned the auxiliary "A" frame.Extensive tests and use in numerous erections produced no furtherfailures.

The ground nail originally planned for use, included a liftingeye for easy removal. However, during the field evaluation testsa lifting eye broke at the weld while the nail was being driveninto the ground by a sledge hammer, In view of this failure,ground nails being supplied (see figure 26) have a straight pin,below the nail head, in lieu of the lifting eye. The nail headshoulder, extending below the pin, prevents the pin from contacting

i

I n Page 4-31

p 22 AV 2 R



1 the support pad. This allows the hook of the "A" frame cable toengage the pin, permitting easy removal from the ground.

One basic lift sling is provided (A - figure 27), by removalof the various extensions, as indicated, the one sling is usedto perform all lifting functions.

I The guy rods as provided are adjustable, with a minimum lengthof 7 feet 3 inches; which length, calculations have proven, isthe minimum acceptable guy length.

Two types of soil anchors are provided for soft and hardsoils. In general the screw type anchor is used whenever possible.The arrowhead type anchor is used when the soil is too hard toaccommodate the screw type. A very comprehensive investigationof soil types, and the anchors required for each type, was con-ducted. In collaboration with the Signal Corps it was decidednot to provide anchors for rocky conditions as specialdrillingtools would be required, or swampy conditions as tho area wouldprobably be inaccessible by truck. Different diameters (8 incheLto 16 inches) of screw anchors were investigated; the 10 Inchdiameter anchor supplied, was found to hold best in most soilconditions. Refer to addendum M for information compiled on allI suitable types of ground anchors.

IIIII

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R 1HAZELTINE CORPORATIONREPORT 10075 Section 4~

I Part d. MISCELLANEOUS

I. Corrosion of some steel parts was observed during the fieldevaluatiob tests; where permissible, these parts will be givenan application of grease.

I 2. All rubber surfaces will not be painted.

3. Inspection of the first servica test model, by Hazeltine, afterthe field evaluation tests revealed loose gaskets and loose rubberbumpers. To prevent future loosening, Eastman 910, a rapid setting,high strength adhesive is now used to secure all rubber items.

L4. The name and number tags identifying the assembly parts origi-nally were decals. these 'hAn•eme loose and full off dCa14k~w Lheevaluation tests. The decals were changed to metal tags and are

I now securely fastened with drive screws.

TASK B. MODIFICATION OF SEELTER

i The shelter modifications were necessitated by the contractualchange requiring Antenna Group OA-1227(XE-I)/TPS to operate-withRadar Surveillance Shelter AN/GSS-I.

This task is divided Into two phases - circuitry and mechanical.The antenna control box (while mounted in the shelter) is suppliedas part of the antenna group. Reference to the control box underTask B is therefore limited to mounting requirements and cablingfor the box,

PHASE 1, CIRCUITRY

Circuitry for the shelter modification is discussed in twoI parts, part a interconnecting box and part b cabling.

Part a. INTERCONNECTING BOX

1. General

To comply with, the specification requirement (to filter all

I

In Page 4-33P22AV2R

I IHAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

i REPORT 10075 Sec *ion 4

I voltage lines entering and leaving the shelter) the interconnectingbox is provided as part of the shelter modification. In additionto filtering the voltage lines, the box provides a onvenienttermination for all antenna to shelter cabling except the rf cable(RF30), thus facilitating assembly and disassembly.

3 2. DesilM

To provide the correct filtering for the interconnecting box,four different types of filters are employed. The filters arepurchased parts from Sprague Electric Co., the four Sprague typesand ratings are as follows:

I 2JX44AI - 2 amp ll-volt 6f-dyc!-

S-68316 - 0.1 amp ll-volt 60-cycle

5 •JX94Z - 5 amp ll-v6lt 400-cycle

5JX27 - 5 amp 50-volt do

I To acoovnnodate the control wiring changes between antennagroups serial numbers 1, 2 and 3 through 7, filters nL909, PL9I0and PL92. were changed from the 0.1 amp, lle-volt, 60-cycle typeto the 2 amp, lib-volt, 60-cycle type.

Part b. CABLINGI 'See figure 21.)

1. General

Cables are not supplied as part of the modification kit.However, cable W29, supplied with Antenna Group OA-1227(XE-I)/TPS,is required for connection of the antenna control box within theshelter. The balance of the cables within the shelter (W10, Wll,W701 and RFP8a) required for the shelter modification are suppliedwith Radar Surveillance Shelter AN/GSS-1.

All cabling design changes in the shelter were in the rf cable.Originally a stranded conductor (Amphenol type 421-103) rf cablewas used. The Fort Bliss, Texas evaluation test proved this cableto be inferior to the solid conductor RG-19/U type. The finaldesign utilizes a section of RG-19/U (RFB54) supplied with shelterN/O~SS-1.

The original design for rf connector (R?901) was for a straightthrough connection, with both connections at right angles to the

in Page 4-34

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shelter wall. Changing rf cable RP30 (See Task A, Phase 1, Part e.)to type RG-19/U, necessitated a right angle connector at the out-side of the 'shelter. Changing this connector permitted the cableto parallel the shelter wall, thus allowing regulation of the solidconductor cable bend radius.

I PHASE 2. MECHANICAL

1. General

iThe mechanical phase of Task B consists of (1) the physicalmodifications required on the shelter wall to accommodate rfconnector (RP901) and the interconnecting box, and (2) installation

of the antenna control box mounting.

All hardware and templates to complete the modification aresupplied as part of the modification kit. In addition cover platesare provided for the wall openings made to accommodate the inter-connecting box and rf connector. These cover plates are for useif the components are removed from the shelter.

I Refer to addendum to Technical Manual for Antenna GroupOA-1227(XE-I)/TPS for final design details of AN/GSS-l modificationfor antenna group.

2. Design

In the original design of the shelter modification (as shippedto Fort Bliss, Texas) the interconnecting box and rf connectoradapter plates were to be attached to the outer wall of the shelterwith rivnuts. The Signal Corps objected to this type of constructionbecause a special tool would be required for installation. To com-ply with the Signal Corps objection, Hazeltine redesigned theinstallation utilizing back-up plates with threaded inserts forI attachment of the adaptor plates to the shelter.

I

I n Page 4-35P* AV 2 R


IXPORT 10075 Section 5

SECTION 5. CONCLUSIONS

The following conclusions presented are the result of evalua-ting the factual data presented in Section 4.

1. REFLECTOR AND FEEDHOMN

The design and construction of the reflector and feedhorn wascarried out by the Donald S. Kennedy Co.

Overall, the performance of the reflector and structuraldesign is adequate. An amendment to the specification was re-quired to finalize the feedhorn design. The specification changefor increased IFF vertical beamwidth actually increased theantenna coverage and enabled meeting the low VSWR requirements.

1 2. ROTARY JOINT

The original specification requirement of 0.4 lbs. permittedloss of pressure per 24 hour period, would have resulted in arotary joint that would have been operating in critical areas.Amending the specification to permit losses of from 1.35 psi to1.675 psi per day enabled the final design of a very satisfactory

i rotary joint.

I

IIII




SECTION 6. OVERALL CONCLUSIONS

Antenna Group OA-1227(XE-1)/TPS has undergone a series oftests that prove the equipment is acceptable for military use.The tests described in Section 4 and Hazeltine Report No. 5122,have subjected the equipment to its operating extremes. No majorfaults or failures have developed during this comprehensive pro-gram. The minor failures that developed, have been corrected soas to preclude any further failure.

The service tests (at Fort Bliss, Texas) performed on theantenna group, tested it in actual operation for a period ofover three months. Preliminary information, on the results ofthese tests, Indicate that equipment performance was satisfactory.

Antenna Group OA-1227(XE-I)/TPS should therefore be con-sidered as an equipment providing satisfactory operation.

IIIIIIII

in Page 6-1

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SECTION 7. RECOMMENDATIONS

While the final design was adequate, certain areas lend them-selves to further improvement. Therefore, the following recommen-dations should be considered for the future:

a. To reduce the pedestal weight it is recommended that:

(1) A rotary joint be fabricated using more aluminumand less brass.

(2) Further tests be conducted with an assembled antenna,simulating extreme specification loading conditions(e.g., ice and wind) to determine If a lower horse-power antenna drive motor Is feasible.

I b. Redesign of the auxiliary "A" frame to enable the truckwinch operator to complete erection of assembled antennawithout use of tag line.

c. For production in quantity it is recommended that thefeedhorn be cast to insure uniformity of patterns andI VSWR losses.

d. To forestall breakage of Indicating lights on the con-tactor box, it is recommended that the pedestal be indentedto receive the box, and a protective cover-supplied.

I1IIIII




SECTION 8. IDENTIFICATION OF KEY PERSONNEL

The following key personnel of Hazeltine Electronics Divisionparticipated in the project described in this report:

John Sinnott Design and Development Supervisor

I Gerold W. Bugen Supervisory Electrical Engineer

Ira Krupen Mechanical Engineering Sectioni Head

Paul L. Dominique Supervisory Mechanical Engineer

IFrank J. Delany Project Administrator

Will'.am F. Gerold Project Administrator

I Donald T. Geiger Ass't Project Administrator

II

I W4ZELTINE ELECTRONICS DIVISIONHazeltine Corporation

Supervisory rechanical Engineer ,eslgn Supervisor•

I Job No. 208

III

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I ?REPORT 10075

IiI

I l~Figure 1, Antems Grocup 0A-1227(XS-I)/TP8

IPage I

P22 AV2RR

"-HAZELTINE 'ELECTRONICS DIVISIONHAZELTINE CORPORATION

REPORT 10075

IFFCABLE

S W20 4,P805SpP804 J805

I

ANTENNA I

PEDESTAL I I ROTARY

22J1 JOINT

I C8,J807 :1: J802PS07 -CPS02

W28'1 P802

SRF 30 IJ803RF30 P803

W27P909

i J 909 4 P9O8

RF9OI INTER-I 10 CONNECTING

f J907SW701 56

i1RF855 W7 . P212

Z.J502 ,' N , ý J212

RECEIVER IFF RECEIVER1

TRANSMITTER TRANISMITTER

I •c•,v•. I 2 I,•.•,RT-212/TPS-ID RT-2,,/TPX

I

Piguee 2. RF Transmisslon Pnths

Page II

P22 AV 2 R

7 ! HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

S~REPORT 10075

coC%

i Figure 3. Assembled Antenna Reflector Page IIIP•22AV 2R


REPORT 100753 36t 35 34 LEFT

LOWER

30 \3 3/ INNER

31

I!

RIHT 1: 4243 4ý44

RI ON _______________ _______INNER 39 6

!

I

LEFTI - UPPER

46 INN ER

50 49 48 47(HOLD)

I •

RIGHTI UPPERINNER 52I

54(HOLDI 5- 56 53 57 7

FigLure 4. Assembling Antenna Refleator (Sheet 1 of 2)

Pege IV

P22 AV ZR


REPORT 10075

65 L EFT

64 76

N 22 AV

72 71

H.AZEL1N ELCTRONICS

DIVISIONI4AZsL11t4 CORPORA'TION

Rs1 PoRT -ioo75

piue5,Pg

29A 2I


REPORT 1OOT7

I500

I /HALF POWER ""ONT

1100

I"

24 22 20 Is 16 14 12 10 S 6 4 2RELATIVE ONE WAY POWER (db) ELEVATION

iI

Figure 6. Antenna Radiatlon Patterns (Sheet 1 of 2)

Page VII

P22 AV 2 R


RBPORT 10075

RELATIVE ONE WAY POWER d4b)

40i-- 40

HALF

IPOINT

11

I I

12

S~AZIMUTH

Figu'e 6. Anternna Radiation Patterns (Sheet 2 of 2)

Page VIII

P an AV a R


REPORT 1oo75

IFFCONNECTOR IRIS

DOORKNO J0

UPPER PRESSURETRANSITION WINDOW

IFF STUB

J COAXIAL -- SPACER

SECTIONI

PEDES TA AIRPRESSUREINLET

00PRESSURE

MATCHING WINDO LOWERMATCHNUB I~ TRANSITION

J807 IRI CHOKE J302 DOORKNOBRF IFFCONNECTOR CONNECTOR

TRANSITION

Figure 7, Rotary Joint Assembly

Page IXP 22 AV 2 Ft


REPORT 1oo75

000 0 FTOIj ~L20ASJ

OSI~ 20A10

0 DS005IOF1041

o000 0 00080

0 00IJIG IO6JI J07 1091 I

Figure 8. Front Panel of Contaotor Box

2 (equipment serial Nos. I and 2)Pge X

P 22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONH-AZELTINE CO'RPORATION

REPORT 10075

FLAT-HEAD SIQISCREW

C3)

SELF-LOCKINGNUT

IIO

I10( SELF-LOCKING

SELFSELF-LOCKING

NUTNU

K10

SELF-LOCSREKSINGOCIN, IU

1(2) NUT(3)

I ~Figure 9. Contactor Box (equi~pment serial Nos.i and 2)

i Page XIP 22 AV 2 Rt


S REPORT 10075 HAZELTINE CORPORATION

I o

0 0 F02ADS107

20A

0 F105

C ©

0 DoIoI©

!0 0 r©r

0~

0 0

Fituse 10. Front Panel of Contactor Box(equipment serial Nos. 3 through 7)

Page X1I


REPORT 10075

FLAT-HEAD SCREW 6101(3)

I SELF-LOCKING

NUTT 1Flo

K10 SEMOUNTING

SCEWI SELF-LOCKING

Q(4)(2()

110SCREWe 110oietr~x(q~petara

(2)s 3 IOugI7I PageKX05PSE22-AVC2IN


.REPORT 10075

ANEN

I mOI EP I EAE1

Figur'e 12. Antenna contr'ol Box

Page xIvP22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONHAZ91LTINE CORPORATION

REPORT 10075

CONTACTOR BOX

12

ANTENNA W25 W23 W22

DRV

J Figure8 13. Antenna Pedestal

Page XVI22 AV 2 Rt


REPORT 10075 HAZELTINE CORPORATION

D0 NEUTRAL CTS2I~ STAR

I Al I 06201

B O RELAY

NO.')-___ ýNO

Al A2IJCRI01- OIL FLOWIBYPASS

OILIFLW1(0 R0 OONTACT0OI4 9101

CONTACTOR

I S604r STOW

FIO4 TOW PLATE

KIOGAS 802 3 2

I MANUALI CRANK

+ - - ---

RIO

05106 r-510K

A~ ----

LRIV

(equipment~~5 aeiKOK . ndaPag-XV

L3 T3 AVZ


I REPORT 10075 HAZELTINE CORPORATION

II

S~CBI01

I I8301 -- 1LO IT3 8701~IN -0---- ~DRIVEI MOTOR

L 2 T2T

8301 0 01 RIOIIFLOW 56KSWITCH R

XDSIOII

NEUTRALNI CRI04 CRI03

"N NO:• !IO CR0 "80

2 CONTACTOR 8804

=9TOFI a•€ Aý f CoI CO0

TIOI

Figure 15. Control Cirouitss Slimplitied Sohematio(equipment aerill Woe. 3 through 7)

J Page XVII

P'22 AV 2 R


REPORT 1OOT7

II

2411 INDICATORI CAM

I SYNCHROM TOMOTOR S612 INDICATOR

I 27V DO POWER- SUPPLY

T102 K104

FO? CORRECTION SYNCHRO

,

II11

ANTENNACAM

I

II Figure 16. 8ynchro. Syitem, Simpllifed Schematic

I Page XVIII

P22 AV 2R


REPORT 10075

A

, __________ _ --__

F104 OILTWTP K103

DS20•- 1_

II

OILFOW NOMAL

III6

Figure 17. Lubrication Heating Control Circuits,Simplified Schematic (equipment

serial Koo. 1 art 2)

Page XIX

P 22 AV 2 n


I REPORlT 10075

II

IF105

C

DS206SOIL TEMP DS202 OIL SLOW 05203INORALI FEE•I •K,03

HEATERCONTROL

L RELAY

S303 HR3OI

SOIL TEMP. IS3 02- 8 JTHERMOSTAT IHEATER

CONTROL •

II TIO I THEIRMOSTLATF ~26

X(106 I SoOIL o

FLOW S203

NEUTRAL

Figure 18. Lubrication Heating Control circuits,Simplified Schematic (equipment

serial Non. 3 through 7)Page XX

P 22 AV 2 R


IREPORT 1075 HAZELTINE CORPORATION

IIIII S805

S! 2i r- - ____j -

"1OFF JAIR PRESSURE ON

DS204 DS205

OFF ON S202

AIR PRESSURE INDICATORS

D

Figure 19. Pressure Control Circuit, SimplifiedSohematic (equipment serial Nos. 1 and 2)

10 n AV aI 0


REPORT 10075

I AIR PRESSURE

DS0 DS204

TIOI

IS805

I L S202

I

Ii0

FFigure 20, Pressure Control Circult, SimplifiedSohemntio (equipment serial Noe. 3 through 7)

Page XXII

P 22,AV 2 R


i REPORT 1007

GROUP SHELTER OA-8OO/GSS-I (NOT SUPPLIED)

AEAOR P R SPART OF AN/GSS-I IANTENNA CONTROL POWER SUPPLY I IFF RECEIVER- RECEIVER"•-I TRANSMITTER TRANSMITTERRT-211/TPX RT-212/TPS-ID

J2 1 4 402 J 4 J2 RF855P20 43 P402 P212

;w2s wi WIo WTOI RF854

IIIP9 '70

I P9901 Lý gIý P~70! J-O7 1 910

INTERCONNECTING BOX -RF91 jJ902 J904 J906 1908E] J909I P902 P904 P906 P908 P909

IDIESELENGINE

GENERATOR SET RF530

(NOT SUPPLIED) W21 W22 W23 W27 25

25 25' 25' 25'

IW 25 4'

W2' P 04 PI05 PI06 P lO4104 JI05 F 106 1i8o

PIO3 1 CONTACTOR BOX MIVO

P109 4803W6 P19 718032FANTENNA PEDESTAL ROTARY

Pool A13-574 (XE- IV/TPS I JOINT4801 P0

Pigure 21. Interoonnaotion Cabling Diagram

Page XXIIIP 22 AV 2 R

HAZEL TI N E.E~ 'VIU'REPORT lOO)7S Hc~rN ROiNICS

I"OA10V S O

p AV


REPORT 10075

0%

Fiue2. AtnaPeetlTastCsPaeIX

P 2A

* HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

I REPORT 10075

I

F AI

I

1 Figuro 214. Auxll•ary "A" Frame

Page XXVI

P 22 AV 2 R


REPORT' 10075

* 4*

coI

IT

Fiue2.BmeIekPaeIXI

PI 2A


REPORT 10075,

I

I a 0 0

o 0

80

I SUPPORT PAD

SCREW ANCHORI

I

I GROUND NAIL

GUY ROD

ARROWHEAD ANCHOR

iFi.gure 26. Miscellaneous Mounting Com~ponents ~ XVI


REPORT 1oo75

A~~ PEEDETLTAAS

II2 0 REFLECTOR ERECTION

I PEDESTAL

I4 4

IC SUPPORT ASSEMBLY3

NOTESI, NUMERALS ON ILLUSTRATION ARE USED FOR REFERENCE

ONLY AND DO NOT APPEAR ON LIFT SLING

2. A LESS 1,2,3 AND 4; ONE LEG TO EACH PICK-UP POINT ON PEDESTAL CASE.

B LEG 3 FOLDED TO "O"RING; LEGS 1 AND 4 TO PEDESTAL. LIFTING EYES

LEG 2 TO BAIL IRON BEHIND ROTARY JOINT.

C LEGS 2 AND 4 NOT USEDI LEGS 1 AND 3 TO PICK-UP POINTS ON SUPPORT ASSEMBLY.

D LEGS I AND4 TO EYES ON AUXILIARY "A" FRAME;LEGS 2 AND 3 TO PICK-UPPOINTS ON FACE OF REFLECTOR.

E LEGS 2 AND 3 TO PICK-UP POINTS AT WIDE END OF FEED SUPPORT%LEG I TO PICK-UP POINT AT APEX OF FEED SUPPORT 4 LEG 4 NOT USED.

IFigur'e 27. Lift Sling Configurations

Page XXAVP 22 AV 2 R

xfT - I08103

OSIb ______ ___________ ___________

s XoSI4 8104 "--/

?/120 ["10 1/ W80

Em D! ,RO,1ba

A CR102

S• CONTRO 1 2 SOK, •, REL v_ I- I / 2 I

4D10 3S0 0

Loio _ 80 q210C

78.. . .. . TBI0 3

J10 1.. 3 80 CR 014 K CR102

- - - < A S " 'a - I N 540"K I, N 54 0

W2SFET I BO

0CONXEIIT NC OUTLDET - 2T810 K TL103

W24 TBI03

COTD CO V NE C OUTLETS _ __ __ __ __ _

I ~~~RELAY____

TI11 a6 I1I) 1 12 611, 21

rA1s 111 4 6]T8002 2lS002 S301

ýTOHELR:MýOSTPAT 11UA C=RANK SWITCWISWANTENNA PEDESTAL OPEN AT IOP 8302- I

AU~b7(XE-Mi.P RJLUIERVIDIR -ms --- - --- -

H)

REPORT 10075

NOTE: CABLES W21,W22,W23 HAVE IDENTICAL CONNECTIONS ON EACH END

CONTACTOR BOX€-, -- ---f

A[ Al A2 v-

D031I03 K102 J13XDSI07 I~IO77

ON RELAY PHONE

2 LI JACK Oslo? .

T 022CCORR TIR-

VOLTAGE

R3 A•cow T 0123 4

--4,K N-4 - -- -

2 1

22 -K T813 I O NTCO KIOI

CROII CR103 Oil TB122-ý 05 5

__KM540FWI -

IB 0 4 YPAS- - -

2 850

T RO.•N54 FLW L4 -_ _ _ _ _ _ _ _ _ _ _ 2_ _ _ S 3 S0 S

5IO J101 A0 1

LANTENNA DV

-----

7i


I- - - -- -

WHNEND r-FLO I NO7MAW21 P9 2 I J9 P901 MI W29 1 ANTENNA DRIVE MOTOR

. . . . .. . . . .I P201 . 01 0l -

IL I~ IA4 oS3A

SYNCHRO CORRECTION I K-< > C, __ I LK I D, - . "-----< Do OS

oKI E

tRECTION I'- " , F Ej-- -- , o4}--j--<.-" I 092 ,oTO-• - -I iFi ..- LOWAK F-I o FL-Z,6j----< F <-- I

2~~ ~ FL 907i IPO

O.-IL 08 203

H (L.ZEAIR 8 202 AIR PRESSURE._. P " --F "s 1-"-< S 1 INDICATORS

10 4 I I 7 8ý •a 10L110 12 1 M )(I -IF 0]+ AIR PRESSURE1S--< -<- - I

, _ _---- - - 23oK K31145? 6ý 78 1 *---[? 1i? [1-12 0820LS -- JF M LII M MP JACK

851N "[L -2 4N< ~ NI501 E ANTENNA CONTROP1906 J9061 - - 11905 P701 r 1 L C- - S-ix--i -TPs

-< : FL 913J M <- M<

53 S2 SI 1 83 S251 -j7: I 6021- - I--< -I-F I_]--Ei--<" 1 ITR4 -24X-400'.••,

, .,-W22 K,- -<---,_--ý9 -L<IK<- K*-I

R8502 4s] RI E "J-FFLSI?717 E <-(EI 31TX4-24 - I- WIo4O ~ ~ ~ 50!8 -~X 6O',,j P904 J9041 93PI P0 J 4031~

5 7 -O"t{:L -<o 11 9-P-

SYNCHRO BOX w w w

K•,-iEf---20] -I-K K I$1--24:1

I I

-880-5.POWER- SUPPLYAZIMUTH RANGEROAR JON NTERCONNECT1NG POWER/P SUIPL I NDICATOR

BOX (NOT !.UPPLiEDL

Fi~zre 28. Overall Electrical Schematic Diagram(equipint aerial Nos. 1 md 2)Page


rFL 9 ,-I I _N R A ISW21 P90201- IJ.0I P901 SO -w21 P902 J92 W29 IANTENNA DRIVE MOTOR I

> •P201 A201

>M I , I IjSYNCHRO C RT I, _ I I -_ - I

P1--D *r-_--i IJ10 I E - I 820 I

C PC <--

"E FL 905 E DR20M(.I L OW7

K F I FLO 90I

4 --- NORMA I-1[F -- ]$I L 2202 AIR PRESSURE

P ~8203 INDICATORS

6, 7 8? 9? .0 it- 12,0_L FL J _- _ AIR PRESSURE I

J,*,I #.+..t.t1"< <-I-[L90"]--j --<4 -- +' -, I F.N-,W23 K F- [ j----< K K -- 02 DI

79 1011 I 121 I I0205- --{M HO JACK

101 N -f-FFL 9121- N (N I ANTENNA CONTROL•II PBo6 .J9061 J95o P701 rM, L- ,2,IxE-,,lTP

"M-- - FL-9•3 M]--- -<m L

"83 82SI L <---[FL 914 .L <- ---< • I6022 4-[F ]<--' - -31<4 -24X-400

RI -- -f-[FeW]lOK 4.- IE.o2~ 1IV.oI

.," -,x-6o0 IPO+f,\ ,I o WIt' PO • 4403 + IW K -F_9_ K <- - --- K ,

R ,I E I I

SHN__*_4._,_•< -[PL,2--4-<H H-< II,,:SP

,- -- --R A

NTITRONCIGPOWER SUPPLY I INDICATORSBOX PPNOHTR BOX WUPPLLED

.gro 28. Overall Eleotrioal Sohematic Diagram(equpm<nt serial Nos. 1 ad 2)

J-ýa e

CH K

xDSIOl

j _____________Al A2 . DAol2 RO- - O------~ 56K

.1-~~ ois-----I : L 1/2 W.l0%

X 1045D104

L. J

JIO? CRO T8103-A CR1N501 CR 102

S8'0831N4 K KIN540

xg~.~ 516T8103 K TBIL..J 0 14 CR103

CE 0J79T 1 540 IN540W24 =F 6o TB103 4

I 30

S CONVENIENCE OUTLETS

I I? TIOI

K103__ _ _ _ _ _ _ _ _ _ _

RELAY_____ ________ __

-- __

W 2 1? 4PT6 T5802 El,) 30

HR 301 OIL TEMP I CAKj FO

ANTENNA PEDESTAL V±2OSA NUL-SWTI-B54X OPEN AT lOF S302THROATj-

AB I4X-)/TPS HEATER CONTR O L GO§AR

JLOI RESERVOIR PM

SPoRT 10075

NOTE: CABLES W21, W22, W23 HAVE IDENTICAL CONNECT

--------------- T- -- - I

Xos'o' CONTACTOR BOX

A2 Dso *10 1 -c-,0 1 SI

I/pw 10% O EA

21.01 A KDS 0

-D L - COTCO II+_TB 2C

480 3 S80 ARO ~O CNATR K

__N ___40 _ K ___ PR0 X 108

IN'4 I- N_4

2 4 6 T B 10 3 K 28 0 KIDS3 7 B O

IN54 - -- N4 FLONHETE NTOLf1A COQA~~ 1 jTHERMOSTATTBI0 PUP------------------------------------------ IN-I 4 YAS-

IATNADRV OO


.3 HAVE IDENTICAL CONNECTIONS ON EACH ENDW2 9,,PJO2 •9••B W9 S• P 20 1 J2

' . . ..L -I-"- .- -.- A P-O1 ---- < ,

CONACORBO P07SYNCHRO CORRECTION I C K K<xDS 07 0r 0Io <2D --< D 01 X E

os~o,, J~oo- -;0_4OS1O0o K104 .D C ]

T10 -02 E8- FL95 -

CORRECTION W --- [VOLTAGE --- < I

2 F IIF<

6 -+FFL"O7T'-1---< 64

21 H.NL HR LB98P 1

T50[ - - _ ]

T 1211,,, 2? 3ý 4 5ý 6ý 7 8 93 1 10 21 11 F

,,! c- , -,- J •" --f I4

F- -- I I 1 <W23 K K-- -<T880I 12 5 m -I- ;"-L----7- ---- NI-1 M-

/I,0 ,<•-- - -il-<-•

I.P906 90. -- - ( " ----<5 P701-r

/~~1 1. N , L __

-5SI24.L|1 • ---- 'L 1OWE

LUV

IW22 K <-L ;916-}LK <j- - -< K*--J R 8502 (I~/ R E <--ý-fjL9]- _--. E <J--(E

'N RI 31TX4-ON R2 EIN O P 40TP 1A A lO8 400'% 21I / 501 31O4 40003P7I 40

0 8 C A P18 I288:1 y 5G-IX-60f'.i P904 J9041 J90 P7 1P403 J4

0%pLS < --- -YH<OX DQF92}( -

INEN DRIV MOTOHRj BOX <NO wSUPPLIED7)w<--

A86 K "4{FL920]-"F K<-J

AH*LLz3kH

8701 IN s3 W A __hROTARY JOINT INTERCONNECTING PP-6RSUPPS I

ANTENNA DRVE MOTOR' Box (NOT SUPPLIED)

Figure 29. overall Electrical Schematic Diagram(equip~mnt serial Nos* 3 throuagh 7)


r.•,• r- - NORMAL -W21 P902 90J'IF 1 9 P901 IW9 I ANTENNA DRIVE MOTOR

. . . - - P201 J201

L -L- ILAI A,SYNCHRO CORRECTION

D 1 -jK D K D9201

.1106 P-10-6- E I026 OLTM P

.1 0 5 D P 1 0 5 7 F L , - H1 :E ,

K - IL ~ J ' 90 LOF

I i >---. I- : _ : ":' -I- <o_

O FL OWo - - -

N H H OIL 09 D203p -- H !SY H (202

AIR PRESSURES• -, -,, "8203 - --- oTORS6, 7, 8• --O 2 " AN N

ICNTI MO

""906 J906 ,_-- [F L 09]- 0- 5 J1 AIR PRE SSURE- IW23

ONK___,L 10F- -

K E-j"LFSI OJ--- < Ko I .1202 DS2057 8 9 10l11 2i- M F1.{FL9HI4 M <M4 . PHNEJACK

50 o 1-{L 9 12]- 0< 0CNTOid-< ~~ANTENNACOTL

P906 Jg91 .J.. ,905 P701 r40 -- i0 LC2911

S3 52 SI ----- L FL 914 .L-. D----• •602,I

-W22 = K (-jL-916 K<- •K

"R--"- 4{FLgs9 W W ;L IE

-~~~R E <, +[•Fý n•'; iI

POWEISUPLY RANG

IR2~

I 0NTER-O6N0, PE0 J9903 P751 P403 40D 0-Fs-eD<

SYNCHRO BOX I -ON N U E4--FF19S T+< W <-< K "-f-[FL 920- K-<-..K

24:

< J4-+EL921 J}4 -< H

I <4{FL 922]H

W! POWER SUPPLY INDIAZUTOR RAGEIINT' INTERCONNECTING PP-674/TPS-1 -ID-41't ID N OIC TRPLIDBox (NOT SUPPLIED) LI4fP0NTSPLE)

Figure 29, Overall Electrical S•hematia Diagram 4(equipwunt aerial Nose 3 through 7) Pag xi


REPORT 10075

ADDENDUM A

VOLTAGE STANDING WAVE RATIO MEASUREMENTS

Figures Al and A2 show the VSWR results of the first modelof final design, figure A3 (block diagram) illustrates the testhook-up for the VSWR messurements in 2, 3, and. below.The searchradar VSWR measurements (figure Al, paragraphs 2 and 3 below)were taken over a frequency range of 1250 to 1350 megacycles.The IFF bands VSWR measurements (figure A2, paragraph 4 below)were taken over frequency ranges of 1000 to 1040 megacycles and

1080 to 1120 megacycles.

1. TEST EQUIPNENT

The signal generator used for the VSWR measurements is aHazeltine Model 1050B, modified to generate frequencies to 1350megacycles. A Hewlett Packard Standing Wave Meter, supplied fromthe slotted line (see figure A3) by a crystal diode detector,provided the indication.

2. ROTARY JOINT INPUT

The VSWR measured at the input to the rotary joint is shownin figure Al. The maximum VSWR measured was 1.32 at 1304 mega-I -.ycle s.

3. RADAR TRANSMITTER OUTPUT

The VSWR as seen at the output of the radar transmitter (seefigure Al) was found by measuring the VSWR into radar cableRF30 (see figure 2). The maximum VSWR measured was 1.45 at 1338megacycles.

4. IFF OUTPUT

The VSWR measurements taken at the output of the IFF system,are shown in figure A2. The maximum VSWR readings were 1.55 at1024 megacycles and 1.73 at 1110 megacycles.

In Page Al

P 22 AV 2 R

HAZELTINE ELECHAZELTINE

DMPORT 10075

. .. . ........

11.6011 .4,11S 61V

----- ---20m m M IT . 1 M M

1.10.

49I 1

+RQEC -H-1

Tiguf Al.Searh 11:1


Appendix A

Iv r MIN -1

I IfTt tl - --. 4

- iiiIM *11 il HI M I - i - Ifl 1 11 tt .itlM1 -Ifil, IIN , .lt qf

M I I 1111] 1:. -t1111Il I111 1W ~ T wtW

111111 if I IiIl l I ' 111f1 IT IIIHT

X- 1 - l*il M111111 MIii~: - .I.211 1Nt- u

4- I.,11fl tI M W l

:fl~ 111 I I v I M1111i1tilMI -011 IjI 1, fuf

A l lf. -11R N -

290 ~ ~ ~ ~ ~ I MI0A1 12 30 3013FREQUINC - 4

Hillr Hl 3e1hRdr yta sW sit

HAZELTINE ELECTROHAZELTINE CORP

REPORT 10075

1,60I ;i ' l i IiT ff i II

Il~jitf p,{ i~ij i

1.50 IiIW .l 1111

I'd 1 ! 11i

I , ' , ifI . 1, 1 1

1.70 -t H+J0011 O -111N111if Hil

U I Tf VN_1111 IIiiii h

1.10--- -Ti ij I i

1000 10M 1Q20 Ill0 V11 10 1H I 06 I7 fl8 1090

t~~~~~~iu' All IN INNr~i V,111-1 :TI IIIHHl


Appen dix A

!MiN! i- ~i H11 ilW:

I**,IiHII I W h d . ... .. .

----- -. I n M 1

I, IT 111111 1 ]H I. 17

I'B U HEN HIU [jlIulIIi!N IITl11 1 11 5 1A 10T 00 ..

n i

K ji0"i!-. =1 = ,:"

4~~~~~1 5 ~I IL.I1

110W7 090 1. 9 1100 Ill N1 1130 (40I1

PRIQEN"I Mil

Fiur A. ~' SitmVS~ ealt CIII ag A


REPORT 10075 Addendum A

Ii

SIGNAL SLOTTED UN RI TOGENERATOR LINE UDEST FREE SPACEI

!I DETECTOR

PROBE

ISWR

METER

I

Figure A3. VSWR Measurements, Blook Diagram

AVPage A4

P Z2 AV 2 R


REPORT 10075

ADDENDUM B

ANTENNA COVERAGE TESTS

The antenna coverage tests were performed by the D. S. KennedyCo., at Cohasset, Massachusetts. The test range is as shown infigure BI. Polarization of the transmitting antenna was adjustedin accordance with the test performed. The antenna under testwas mounted on a tower approximately 30 feet high in its normalattitude for azimuth patterns and endwise for elevation patterns.Signals received by the antenna, being tested, were bolometerdetected and recorded, see figures B2 through B21.

Paragraphs I through 6 below describe the antenna coveragetests, and give the results, for the first test model. Table BItabulates the half-power beamwidths at the mid-point of eachband (in both E and H planes) for test models, serial numbers 2through 7.

1. ANTENNA GAIN

The gain of the antenna was measured at 1300 megacycles bythe substitution method. That is, a standard horn of knownabsolute value was substituted for the antenna under test, bothreceiving the same maximum signal and the same detecting systembeing employed. The gain of the antenna was calculated asfollows:

Gain of antenna above standard 20.10 db

Gain of standard above isotropic 14.11 db

34.21 db

2. BEAM ANGIE ABOVE HORIZON

The beam angles above the horizon in the two In? frequencybands and at the mid-point of the search radar band were takenas follows:

a. The antenna was leveled in the normal position.

b. A transit was mounted to the reflector support, so thatits azimuth plane was parallel to the reference plane.The transit elevation scale was adjusted to zero degreeswith the telescope level.

c. The reflector was turned 90 degrees, so that it "stood"on end.

I

In Page Blp 2, AV R R


REPORT 10075 Addendum B

d. The antenna was tilted and trained for maximum received

signal and a reading recorded.

j e. The antenna was then trained for a half-power reading.

f. The telescope on the transit was adjusted in the elevationp1gne until the edge of the transmitting antenna wassighted. The scale reading of the transit then recorded.

g. The antenna was rotated in its elevation plane until theopposite half-power reading was obtained.

h. The transit was again adjusted as in f above.

i. The upper and lower 3 db points (half-power) were added.One half of this angle was then subtracted from the upper3 db point to obtain the beam angle above the horizon.

3. The results of the tests are tabulated below:

Frequency Beam. angle above horizon

1300 megacycles 2 degrees 45 minutes1001 5 megacycles 3 degrees 46 minutes1118:5 megacycles 3 degrees 37 minutes

3. AZIMUTH PATTERNS

Figures B2 through B8 show the principal plane horizontalpatterns measured in both the search radar and IFF bands. Thefollowing is a summary of the half-power beamwidths and sidelobe levels:

Hulf-power Side lobeFrequency beamwidths level

(megacycles) (desrees) (db down)

Search 1250 1.6 28.0Sear 1300 1.6 29.7Radar 1350 1.5 28.4J.

1001.5 1.8 25.91035.5 1.8 26.9I 1061.5 1.6 27.91118.5 1.6 26.9

In Page B2P 22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONHAZIELTI NE: CORPORATION


4. BACK RADIATION

Back radiation (figure B9) was measured by recording a 360degree azimuth pattern. The radiation in the vicinity of 1l0degrees from the main lobe is at least 33 db below the peak.

5. AZIMUTH SIDE LOBES ABOVE AND BELOW 2.5 DEGREES

The azimuth side lobes off the principal plane were checkedby measuring horizontal patterns at specific tilt angles. Theantenna was tilted sufficiently to determine the greatest intensityof side lobes whose maximums do not lie in the principal plane ofthe main lobe.

The azimuth side lobe patterns are given in figures B10 throughB14. The power of the highest side lobe with respect to thereference power level of the main lobe is noted on the patterns.

6. ELEVATION PATTERNS

The elevation patterns (figures B15 through B21) were takenwith the antenna oriented to stand on end. The principal planevertical patterns were measured for the search radar and IFFfrequency bands. The specification limit for vertical shapingis shown overlaid on figure B16.

TABLE BI. HALF-POWER BEAMWIDTHS

TEST MODEL H PLANE E PLANE(serial number) (frequency in megacycles) (frequency in megacyoles)

1020 110aI1300 1.020" 1100 1300

2 1.830 1.70 1.670 7.90 8.20 5.80

3 1.870 1.770 1.670 8.130 8.270 5.830

4 1.830 1.730 1.70 8.130 8.2o 5.8°

5 1.830 1.730 1.670 8.470 8.20 6.00

6 1.800 1.770 1.630 8.20 8.20 5.830

67 1.877 . 1.670 8.070 8.10 5.970

II

In Page B3

P 22 AV 2 R



ANTENNA(40 FT WIDE AND II

I FT HIGH) UNDER TESTrAND POWER SENSINGRECORDING EQUIPMENT

STRANSMITTING ANTENNA ,,.,-,-

(CIRCULAR SECTION OF A"'-- S~PARABOLA WITH A 2a FOOT

jDIAMETER)

I

40,35 FT

II

Figurb Bl.o Antenna Test Range

Page B4

IP 22 AV 2 R

HAZELTINEHE

I REPORT 10075

2 2

1w -2

IF .2l.- I

4 1 --8-

II;. 6 ,11 tA O

14 2 60

CHAPTANGLE

I PFigar. B2. Horistontl Pi

HAZELTINE ELECTRONICS DIVISION.HAZELTINE CORPORATION

Appendix B

-- PATTERN No. VATE2-4-59 I--j-

PROJECT

ENGRS.4 REMARKS

6 1250 mcE PLANE

7F]A 11 ---- -- 11111 1 8

iý 6L

36t

ANLE~ CI~trI ALNT N ALAA

14HI

I Fiilr I2 -4"Tota Fat[n SerH Radarl0 gayeiPg.B

HAZELTI I

ImpORT 1WO?5

44

--- ------ - W 4 w IV

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I -

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I [I 1. -

F! 1 F 12'72 36 1-1

L.g~r 11 3ll I on

HAZELTINE ELECTRONICS DIVISIONHAZELTINE~ CORPORATION

Appendix B

PATTERN No. DATE2a-5-59~ LtPROJECT- - ENGIRS.

4 REMARKS

t1- - f-R 130MC

6~ EPLANE

IIH~ I -----

1111 1 - ---------- -

TI I j I >

.1..-Rff ----- -'1 -1i

AIT II

T1-712

60 8-1 1

44 I- I-r -14

ANGLE I6f2-__ ______

Figuz~~~~~ ~~~~ 9 3.drm na )atr , S ac Rd w 3 0)gaca ae 3

I HAZELTINE ELHAZEL

REPORT 1007%

8-

A-8

j14 1 t- 14

t~o -IFr I 4t 72

0


Appaidix B

----- PATTERN NO. DATE2-4-59

it T

8

II

- - -4I ffti-1-1-i t *

~ nitI --

Oj- jO -L 8

-ý + f ------- ~612 - 20 3Q

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HAZELTI NEE

HAZEL

REPORT IL0075

0

ft

-4- 1 -

-- -. ----- r _.I I - - --- I M __ __

I --- -- ---l-- I- --t -t 1- 1-. .. * -Ii

II, I TIll

'A-RFip~s E. HrlotaP


Appendix B

-- PATTERN No. DATE 2-5-59

2 PROJECTENGRS. ______

REMARKS

- - 1100 1.5 mc

~-t. PLANEt

-- K14-- i-I I- H -1 U

Ilk IR'tI 1-MrI H.1..I....I

ItI _ __ j _ I

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ANLTNVI O 2

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HAZELTINE ElHAZELI

REPORT 10075

1 -1

j1-h 'Lii HH

I I 1ti- 1 1--11ld t ;j

IT II

Ili~~ IT I1i111

2-- I~ T 1

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Figur 1 6 orICI a2


Appendix B

HT-

H I I I lli, I I

I 'l l i -hI F- 11: - IFFM

I AI I [F-Tf, H H 1

i ll I II ItI -I V

.ilIIilIlI 101111 iIH~ 1 1'i-IT I

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tili

lii' Ii ! 111 IM il

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ANGL0 4 -1 -_4IU~3 C~NIIAhNA N..ALNA ~RIFigure~~~~~~~~~~~~~1 46 oiotlPten ' laa,13. ~o~~ ae

HAZELTIN

IMPORT 10075

1-12141

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-~~~~1 _'--h. l

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Figure B7. Horl


Appen dix B

-0PATTERN No. DATEg.5.sgj

2 PROJECT.. T jI ENGRS._

4 REMARKS

T II 6. 1001.5___

I IH

I~ I t ~i I-

I (tF1I I I--- - +W--- - I 1' -1- 1- 1--] -t l

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IMP0M 10075

S I-

II - --- - F M R

m - t[4 i

F 4F- ~ -* ---. ~ - A M-

C - IR 101

LL, 12R 36 --

P4uz 8.Hz'unt.


Appendix 9

PATTERN No. DATE a~a. a,

-- PROJECT----- ----- ENGRS.

4- REMARKS4 1S.

MCH PLANE

-f F ------ V

ITHifH1ji 1iii41t]1ttIThth4t17 17 - - - -

F n 11 0

l-I 1...

360441Ifi tR- i*1441I-

ANGLE~~--- ATAT, ER

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IMPORT 10075

-IZ

4J If t -4 - - tilrIT. - f -r- +I I

---- -- M 1* 1 t w - ot6

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8 70H~

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Appendix B

-1-K-0-_T PATTERN No. DATE 2.4-59 LI-ITF PROJECT-F . ENSRS.

REMARKS

I~~~ - -L6 PLANE

f -- -1-1

- --- ---- -~ _fid f

11 ff I- N .1 -

1-11 T~ if1ifi W I - J t*1

fl -L - I -- -- -H t tfN IIjio~i 440j ___ rl

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I1 111 1 1 4i l I II I IL 6--

87I I7

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1\ 111Y 1 606

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t-ay Milluu~h i


Appndix B

PATTERN No. DATEa-s-5-a1*04R IFF HIMPROJECT

ENGRS.4 REMARKS

X ,T W6 1 1t' DOWN TILT--

8tt

T_-N __ 1 1, 1 1 1 11 - I I III2I I

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I N0AN L 3I~t~C-?ANA IC. TANA

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IMPORT 10075

It14L1

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It lt6 1 t t - tI - .r t+ I

0H _ - 1 -- -1- t

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IL I 1 ,1 I -ii l

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Appen dix B

0 - PATTERN No. DATE 2-5-89 T

2Q 4 PROJECT4. Et __ENGRS.

4 REMARKS

-1-1300 MC- 6---0 20 DOWN T ILT

-- -- 14+4 rt-r

L I IL'I I

+-6

4-H -

a- 40 T

T h idLftl~~ll~I~lI---4 -d4~~ CHAlRTN.1 FlLE81 CETP.AAtA N.TAT.OORH

F 11 -AN 4 [-- r h

Figure~~~~~~ 4L.A iti Bd oe Pat r , 2 D ~ T 3tp

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I DPORT 10075

IH - L-

8-L

h - I - Mt

P-I

__. -t - F I. -

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11gurt B12o Aisuth 5%


Appendix B

PATTERN No. DATE a.-5-9S -

-- -- - - - - -PROJECT IENGRS.

4 REMARKS

9 N ~ IT. I 1- 111

t tl"T. II-rr--rnit . ------- 1300m 7C-- -- - ]a UP TILT

i-I T-I-ITI Ih I II-I-Ul-A11 '1:2.41 -1A-

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IT IIiI I II HH I 'Ii

-lil 1 11 - t l

6 ll i HL-.Hm I Hiil

40 CANT o. 1t 11CIEN¶~IfC. ATANTA. INC.. ATLANTA. GEORGIA

ANGVLE

Figure, B12. Aslaith Side Lobe Pattern, 10 Up Til C*# a BIS

HAZELTINE ELECTRONICS DIVISIONHAZIELTINE CORPORATION

Appendix B

0a -- -- --- PATTERN No. DATE 24-589

PROJECT

_ENGRS.--- REMARKS

F E ý'ý 1 L E_ IFT ( IT - - - -- - - - - -

F - --- --

41~~~~~~~ IT-FF~TII

4! -----

4 Id111 if II it I II- .-. I -m* *T

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Iikh -1 11 J,-{fl

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06 La

-- - 3601720:1- MARVNQ.

ANGLE H~ Hti7It-TLNA tif. A-ANA OtO11-

Figui,111 512. As-mtki 111 111Patr, 0UpT

HAZELTINE

IMPORT 10075 A

It ýf*Rflt-- ----It h ~ T _

4-lq-- 111j,_44_l

'V1

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-A lf -II .- 1

1-~ ---- f. H t 11..IA T

01 0

Figare B13. "rI


Appendix 3

n -tPATTERN No. DATEZ-5-59

2- PROJECT

- --- -------- ENGRS.

--- REMARKS

ti 1300 MC

- + -~26 UP TILT

It 1 -if i - I I-

I ]TI

I~ ~~ -r -IIk--M

I ~ 1Iti I 1 1 1-61

i 20

c; __. 1 2 Id -1 8

IE -1-- l ---- 4-.-- C

ANGL MART NO. 121 SCIENTIFIC- ATLANTA. INC.. ATLANTA. GO0R8IA

Fi.gure 313. Asiiith Side Lctbe Patterns 20 Up Tilt CE1mm4 . Page B16

HAZELTI NE

REPORT 10075 H

6X RUE NCE -

--- -- -- - -- --

. . .- - - -..

..... -T I

1H II t

_H4.. --

It20 -1--

?1gAW M


Appendix B

--- PATTERN No. DATE a-5-59 _

2 PROJECT

-t - - - - -- -[_ ' - - i I- -- ENGRS. Li4 REMARKS TF I

I r 11 r .. ... 1300 MC-1 1ENE - - - - - - 30 UP TILT

I - - V-8

1- t 4_H -1- -K 2

I~ I+ I14

I' - -- - - - - --~-- ok

Tl Ila _

I IT

-A

ANGLE __ -_H

Figure B14,. Aiim~th Side Lode Patterns 30 UP Til t C%4 Page B17

I HAZELTINEHAZE

Iýr illE 1OO7,

--- - ----- - _R I2--

F1ill I I

4,1 , 1 1 1 I 11 7

It - 1Tt~1

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Appe ndix B

Ii I lii I tiF I.-I PATTERN No. DATEI-25-59 J.1 T~ Tf 't4J I LIliii I~Ji 2111I PROJECT i I. I

_____I_____ IIii lii' ' II I REM~ARKS fl ii ~i

1-7Fi 1i II ELEVATION PATTERN liii YII

-11 -1 r 1 --

1 8 I It t -

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h il I ii !.1 I .lll II i I -! i If~

111 I iwIi I I Hlu I __ H 1__1_; 1111TI-

I

120 II

-- - - I-- I- 60f

Figirie B15, Elevation Pattern,, Search Radar# 1250 Mengacycles Page Be1

HAZELTINEI HAZýREPORT 1OO75

0. 0

Il~lt- _--Ii--t1 9R-rf1RI-rm W,

III T FU III I- 6

ii-I- _1 nd- H- 1

FIl ili -1 'Ih -11--.4

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1_0

-itv d-f , I - It -- 1 -1 1 - I H4 It 31 6. 3 v t


Appendix B

Ht1 PATTERN NO. DATEi-2g-59PROJECT2

Ii L IENGRS.I ~REMARKS4

H II'' I Vl - - - - ELEVATION PATTERN-II __6

81. 8{] -1 -

illil I I I

.I ......~ .I. . i.

I0 I I

I11 11 1 H I

fl-~ - - ff I Il

_H_ ii Ii'i,

61111 ' 1<4T 1iI~ ii Jl 1 I

Ii TMJ - 0 140 7.

Figure B16. slavation patterns search Radars 1300 ?4.gacyosb Page B19

I ~HAZELTI NEHAZ

I RIPORT 10075

22

TIiF ,MT IA i ;-I f

iiilld1hltl jj

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IM

1 ?±g~~e B7* 6-


Appendi x B

PATTERN No. DAE12 - --

2 --- PROJECT2--- -- - ENGRS.

4 ~REMARKS4I I LW I Li ELEVATION PATTERN - --

I RI 1 150i

Wi IFI TIT H'I

liii F!Il 111

11 ii I 6

ii~ II, It~ i~I -. 11 H--1 I- II 111 Ft

LIF I ij' I I I d1

I II 1~ i 'ii*i ' iI~~w1Il i ~ j 11 , 1 ii H IM 11 F i

JIi 1 m I- I l i i

CHART No.121 -- 11IC. ATLANTA. INC.. ATLANTA. GKOffOIA

Figure B17, zlevation Pattern, Seaomh Radars, 1350 Megaoyc~Jas Page B20

HAZELTINEHAZI

IM PORT 100O75

4it 4.ýI 4ýf 1

fi N -144 ------- IN

HI 1 11- 4 -- t4 11-

-1t

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----- lit--~L I .

I-E I 1 .16 -

I -C

I~~~~~ 72j~4 ~¶IH -11-1-1 ANLH6 - 72 IIi-. iW

th~~ipr U ~ 8 it..-i ,1


Appendiz B

00N HPATTERN No. DATE 1-95

PROJECT2

ENGRS.--.....- - - -4 ~REMARKS4

-4--- --- "T ELEVATION PATTERN6100115 me 611 1 1 1

E PLANE I

8F

I- 4H Atl d t-11 11 11 11 I ( 6lT

f1 -ITI it

a: -FF. 1 4I *---i Iti f.j l H E _ I 6-- -- - - -- - - -

j t .' _R .. - - -------

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IMPORT 10075

I0I

III A '4111

HHI- tr 1j~- tR- f-t6-

it 1. Im w iji

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J j J l I 9 1 ! j l ii j~{jllAO6, li

121, ANGLE

IFigure Big. Elevat loll

Imm


Appendi x B

0--- - - -PATTERN No. DATE 1-29-59

-- PROJECT 2 1 t71, ~~~~ENGRS. 1--t

4REMARKS 4.--t H d -1I-.-

ELEVATION ATRit 10-8F a iNPATENt ----- -T- .11 - ---i .

--

I I ý j I - - I - - - - - -I

HfIj if~JI0 -I ' I. -1

I I - 11 T-T-11-- 1 --- -- - -ii

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I ~HAZELTI NE

HAZ

I IMPORT 10075

II I 7 1 1 1 1 1 ... 1IIIIHIII i m IIIII , U TO '

II- ~ I I -M t -- F4 t

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]I --- ?t l gu 120i .El v to a

1I1 -1 --1 H IS TI -- --it -4 .- t f - il 11iLýi


Appendix B

PATTERN No. DATE 1-29-59 SA2 PROJECT

ENGRS.

4REMARKS -- - - - -

- - I ij - 6ELEVATION PATTERN ------

M II I I .

Jii flit --- I---------------------------------------------

H_ ------- - -II

HI tiff1L -tf-H r - - --

I I i l

FIW10.Esato aten 1 aar O1. baou. Pgz

HAZELTIN EH4AZE

UEPOIC107

IT I 1

-FI

TI4

2ih R 1 I if.1 t

1,1 H1!i

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Appendix B

PATTERN No. DATEiz- M 1M -f m - 114 1PROJECT 2-ENGRS,REMARKS4

It - 44 --- MW - - - ELEVATION PATTERN tI 1

E PLANE

I Itl

I 8-

H I- II- I 11-- -- --

>i l'iilU

4I 1- - , JI

fdfuf - -----' --

-ILLj 18

4 C.A.T o.1 RI K!NTIFIC.A7LANTA. INC.. ATLANTA. GEORGIA

Figwaze Wi, Esuvation Pattemu, iF? Radar9 1118.5 )bac3clas page Bzi


REPORT 10075

J ADDENDUM C

ROTARY JOINT HIGH POWER TEST

This test was conducted at the Rome Air Development Center,Rome, New York. The rotary joint was connected as shown infigure Cl. The high power radar signal was supplied by amagnetron with an RG-b9 waveguide output. The power divider onthe output of the magnetron provided power output control. Powerwas measured with a high-power water-calorimeter load.

A double stub waveguide tuner was connected on the rotaryjoint output and the water-calorimeter load connected to thewaveguide tuner. The output of a test generator was fed, througha 10 db attenuator and a waveguide slotted line, to the inputof the rotary joint. The double stub tuner was then adjusted toprovide a VSWR of 1.3 in the slotted line. The test generatorand slotted line was then removed and the input of the jointconnected to the magnetron.

The magnetron trigger circuit was adjusted to produce pulses4 microseconds wide at a PRF of 225 pulses per second. Therefore,to obtain a peak power of 2 megawatts, an average power of 1800watts must be obtained, since:

PayP (Pulse width) (Pulse Repetition Rate)

where, P is peak power in megawatts and Pay isp

average power in watts

then pulse width can be given in microseconds,1800

that is, Pp = ( = 2 megawatts

The average power of 1800 watts would be measured on thecalorimeter by a temperature difference on the two thermometersof 3.4 degrees C in accordance with the following calorimeterformula:

Pav= Q (• T) 264

where 01 = water flow (gallons/minute)

4 T = temperature difference (degrees C)

Pay = average power (watts)

therefora, Pev (2) (3.1d) (2614) = 17,5 watts

In ?a',c ,:

P 21 AV 2 R


I HAZELTINE CORPORATIONREPORT lOO7• Addendum C

I The rotary joint wea evaouted to a gauge pressure of 6.7 psi(representing an altitude of 16,000 feet above sea level). Powerwae transmitted through the joint for a period of 15 minutes,during which time no adverse conditions were noted.

rI

Iin Page C2P 22 AV 2 R



REPORT 10075 Addendum C

4I

ROTARY TUNER LOAD

PSR POWER DIVIDER

JOINtTl *---INPUT LoAD

TO

MAGNETRON

SLOTTED

-------------------------------------- . db SIGNALGENERATOR

Figure Cl. Rotary Joint, High Power Test

Page C3

P 22 AV 2R


SREPORT l0075

ADDENDUM D

DESIGN OF OVERSIZED "0" RINGS

During pressure tests of the rotary joints, air leakageoccurred at the pressure window flanges, with the pressurewindows mounted in the normal manner. Flat plates, when sub-stituted for the pressure windows, showed no evidence of leakage.A subsequent investigation of the pressure window and "0" ringgroove design revealed that the leakage could be considerablyslowed by placing a shim in the groove beneath the "0" ring.

According to manufacturer's design standards, the groove forthis size "O• ring (.139 t .00I Inch) should be out to suchdepth as to provide a minimum squeeze" on the "0"1 ring of 0.025inch. The groove, being 0.100 inch deep, should provide a mini-mum of 0.035 inch of "squeeze," more than adequate for propersealing. However, this assumes that the window acts as a rigidflat plate. Since the leakage has persisted, it has been attri-buted to some deflection phenomena existing in the pressure windowassembly.

In the worst case, the leakage was completely halted byplacing a 0.030 inch shim beneath the "0" ring, thereby decreasingthe groove depth by this amount. Thus, the theoretical "flatplate squeeze would be increased to 0.065 Inch.

The same amount of "squeeze" may be obtained by increasingthe cross sectional diameter of the "0" ring to 0.165 inch andusing it in the standard groove of 0.100 Inch depth. By usingthis non-standard size "0" ring, the amount of squeeze requiredfor proper sealing was obtained and the need for an extraneouspart, the shim, has been eliminated.

The oversized "0" ring was molded by the Mechanical RubberCompany, Warwick, N. Yo in accordance with the optimum dimensions

I calculated by Haseltine Blectrenle Division as follows:

"O" RING DESIGN CALCULATIONS

COros Sectional Areas:

S- Standard sized groove AG w .171 x .100 w 0.0171 In*

2 - Standard "0" ring (139 die.) A0 V(.139)2_ 0.0152 In?

3 - Shims, As (max.) = .171 x .0030 - 0.0051 ip,AS (med.) a .171 x .0025 0 o.00oi3 in?As (,m.) a .171 x .0020 0.003 in?

in Page Dl

P 22 AV 2 R


I RPOR! l007• Addendum D

Ratio or 3xoss-a Rubber to Available Igaoe (R):

I - Maximum case:

R a o - (AG - As (max.)) , 0.0152 - (0.0171 - 0.00%2)AG - AS 0.0171 - 0.0052

S001 2 - 010120- 0 003 20.0120 0.0120

2 - Median case:

o.oM12 - 0.0128 0,002L 1o

R = 0.0128 0.0128 = 19%

3 - Minimum cases

0.0112 --. 00137 0.0015

0.0137 0.0137

SYNTITSIZED DESIGN ORITERIA

Method It Design overszsed "0" ring for median case of excess

rubber to available space ratio.

AG a .00171 In2 R = 19%

Ao a AG + 19% A a A( (1+ 0.19) (0-.0171) (1.19)

A0 a 2.04. x i0" 2 jn, . fl

dm =A 0 - \(0(2.% x 2lO2) a \f.6 x 10-1

d m 0,160 Inch

I

In Page D2P 22 AV 2 R

t HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

ERPORT l007• Addendum D

Method II: Design oversized "0" ring for median case where itscross sectional area is equal to the total crosssectional area of the standard "0" ring and medianshim.

A0 = A0 + As(med.) a 0.0152 + 0.0043 w 0.0195 inn

d = fj(Alý x0 F* 248 x 10-1 = 1.575 x lo-3.1U

d = 0.158 inch

The diameters computed in both methods I and 1I are approxi-mately equal and should constitute the median size required forsealing the pressure windows. Therefore, a diameter of 0.150 I.005 inch has been selected for the oversized "0" ring.

Subsequent air pressure imerslon tests, using the oversized"0" ring in conjunction with the rotary Joint and Airtronpressure windows, showed positive results.

In all cases they:

1. Fit the groove quite well without extruding when theflange bolts were taken up tightly.

2. Effectively eliminated the leakage of air through thepressure windows. This fact Is supported also by theresults of the heat run conducted on antenna pedestalserial nuber 3, In which the rotary joint was sealedat the pressure window flanges with the oversize "0"rings.

During the 24-hour period from 10:30 A.M. 9/26/60 to 10:30 A.M.9/27/60, the total pressure drop due to air leakage was only 0.1pas, well within the specified limit of 1.68 pai/day.

I

ln Page D3

P 22 AV 2 R


REPORT 10075 Addendum D

PERFORMANCE DATA SHEETOA-1227 ANTENNA PEDESTAL

SERIAL NOMBER 3, 24-HOUR BEAT RUN

PressureTime Temp. 0C (PSIA) Results

S10:30 17 15.05 Sinoe the terminal temperature

11130 19 15.1 readings are equal, the air

12:30 21 15.4 leakage loss is the difference

1230 22 15.6 In the terminal pressures, no

2:30 24 15.8 -temperature correction being

3:30 required.

4:30 26 16.0 P initial - P final a Leakage Rate

5:30 25 16.0 Elapsed time

6:30 24 15.9 15.05 1DsI - l-1.90 psia = 0.15

7:30 23 15.7 24 Hours PSI/Day

8:30 20 15.4

9:30 20 15.2

10:30 19 15.1

11:30 17 15.0

7:30 am 18.5 15.0

8:30 17 14.9

9:30 17 14.910:30 17 14.9

I

in Page D4P 22 AV 2 R

"HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

IREPORT 10075

ADDENDUM E

ROTARY JOINT, ANTENWA GROUP OA-1227(XN-1)/TPSSUMMARY OF 2L HOUR CONTINUOUS PRESSURE TEST

In compliance with paragraph 3.3.2.10 of SCL-5296, provisionshave been made for pressurizing the rotating Joint to 30 poundsper square inch, absolute pressure.

The rotary joint has been tested while continuously rotatingover a period of 24 hours, and Its leakage rate calculated asfollows:

The initial air pressure within the system (pl) was 15.0 psigand the air temperature (tj) was 29.30C. At the conclusion of theteat (P2) was 13.7 psig an• (t 2 ) was 26.500. Although the pres-sure gauge readings show a pressure drop of 1.3 psi, It must benoted that there was also an accompanying drop in temperature.In correcting for the temperature differential, the readings mustall be converted to absolute scales. Thus:

PI = Pi + 1i.72 - 29.72 psia T, - tI + 273 a 302.3 0K

P2 a 13.7 + 14.72 - 28.42 pisa T2 - 26.5 + 273 - 299.50K

then the Ideal final pressure (P21 ) corresponding to (T2 ) Is cal-

culated using the constant volune equation for changing conditionsin one gas.

P PITs ,, (2 .7 )299._0 K) = 29.4.5 psleTI 302.3 0K

By subtracting the actual final pressure gauge reading from thisvalue, the amount of air leakage in psi may be found. Hence:

Air Leakage a P2 1 - P2 = 29.45 - 28.4.2 - 1.03 psi.

Article 18 of the second amendment (February 2, 1958) to para-graph 3.3.2.10 specifies: "The leakage rate for the joint shallnot allow a loss of pressure in excess of 0.b. psi in a 24 hourinterval." Obviously the tested leakage of 1.03 pai was muchgreater than the 0.4 psi per day allowed by the above amendment.In view of the basic design factors influencing the performanceof the Joint, it was Hazeltinets contention that the above speci-fication is overly stringent and disproportionate with reasona-bility of design. Following are some of the design limitationsbhioh must be respected:

I n Page El

P 22 AV 2 R



REPORT 10075 Addendum E

1. By stiffening the bellows, which would Increase the sealingpressure, the leakage could be reduced. However, thereis a maximum limiting surface pressure at which sealwearlife is sacrificed for a little less leakage. We havedesigned our rotary seal bellows joint to function safelybelow this limit.

2. Conceivably, the fine finish on the sealing surfaces (flatwithin two light bands) could be made finer, but a harder,closer grained material would be needed. A compromise wasaffected here by using a high grade graphite ring withsuperior qualities of long wear and natural lubrication.

3. Another design factor involved is that of the total life ofthe air tank at a given leakage rate. Rather than Impairthe effectiveness of the rotary joint by obliging It tooperate under critical conditions, Hazeltine chose todesign for a tank with a longer service life, and a sub-stantial factor of safety for pressure loss. The air tankhas a capacity of 386 ou. inches, and a service pressureof 2100 psig. Assume that during the service life of thetank, that its pressure will drop from 2100 paig to equalizewith that of the system at 30 psis.

Air Tank Rotary Joint

P1 a 2100 psig a 2115 pals P2 = 30 psiav1 a 386 in, V2 =%•7o in 3

Assume that atmospherio pressure = 15 pals

Since the air will stop exhausting from the tank when itspressure reaches equilibrium with that of the rotary joint itspressure differential (Pdý vill be 2115 Pala 30 psl. - 2085 psi

rd d = P2v2

, Vi= (2085 psi) (386 ,dn) = 26,800 in 3P• 30 Polo

V is the volume that the air in the tank would occupyat 30 psi_ inaide the rotary joint. Initially the rotary joi•tcontains 750 in3 air at 15 psi. wilch is equivalent to 375 inAat 30 pals. Therefore, at 30 posi, the air tank is capable cecompletely filling the rotary joint 35 times.

26800 - 375 2642-5 35;.2575= 750

ln Page E2

P 22 AV 2 R


I HAZELTINE CORPORATION


i At the specIfied leakage rata of 0.4 pal per day, which Isequal to 10 cubic Inches of air lost from the rotary joint perday, the rotary Joint may be completely exhausted In 1800 hours.

(o.4 psl/day) (7•0 in)) a 10 ln 3 /day air lostI 30 pals

.750 idhre

0 in3 x ,. day = 1800oo hours

10 1n3/day

Since the rotary joint will never exhaust below atmospherlopressure (15 pals) only one half of Its volume of air will leakout. Thus the time to exhaust the rotary joint to equilibrium

with the atmosphere will be 900 hours at the specified rate ofleakage.

1800 hours/vol. x vl - 900 hours12Thus when the rotary joint is being filled to 30 pala, the tank

must supply one-half of its volume of air. The tank has alreadybeen shown to be capable of completely filling the rotary joint35 times. Therefore, It is capable of half-filling the rotaryJoint 70 times.

Thus the tank would become exhausted to equilibrium with therotary Joint at 30 pala in:

I L w 900 hours x 70 - 63,000 hours

Hence at the specified leakage rate of O.4 psi/day, the tankin capable of a service life of 63,000 hours running time.

As specified in paragraph 3.7.2(a) of SCL-5296, the overhaullife of the unit is 5,000 hours of operation at 23 hours per day.By comparing the two figures, it becomes apparent that the tanklife, at the specified allowable leakage rates is 12.6 timesgreater than the overhaul life of the unit.

At the tested rate of 1.03 psi per day, the air tank lifewould be:

would L a 63.000 x 0,'- = 24,450 hours1.03

I which Is 4.9 times the overhaul life.

In Page E3P 22 AV 2 R

UU HAZELTINE ELECTRONICS DIVISION



To account for the inevitable variations in resllience andfinish among the seals (1 t 15% tolerance in surface pressures)a leakage factor of 30% may be added, assuming that the optimummealas testedjleaks at a rate of 1.03 psi per day. The leakagerato would then be:

A r - 1.03 + (0.30) (1.03) a 1.34 pal/day

A consideration must be made of the varying conditions enooun-tered in operating and maneuvering in the field. The unit isdesigned to operate continuously for 23 of 2Z hours per day for5000 opetating hours. We realize, however, that there will mostlikely be periods of intermittent shut down when the equipmentIsn't operating, but the seal is under pressure and will lose airthrough static leakage. Then too, it may at time become necessaryto reposition the unit in the field for tactical reasons. Thiswould necessitate closing off the tank air supply and breakingthe unit down for transportable packaging. During transportation,the unit would be subjected to extended and irregular vibration,enhancing the possibility of additional leakage. Thus, a liberalfactor of safety for pressure loss, as we now have, is advisableto offset the possibility of unanticipated loss of air; and aswell, the adverse leakage affects of operation in elevated tropical

I temperatures.

To account for these variable factors, the leakage rate hasI been further increased by 25% giving a figure of:

r = 1.34 + (.25) (1.34) - 1.68 pal/day

j The tank life at this rate would be

L a 63,000 x OAk 15,000 hours1.68

The factor of safety for tank life over equipment overhaul lifeIs now:

Sp. =- 15.000 hours = 3.0I •,500 hours

A realistic evaluation of the leakage problem has shown thatthe use of 1.68 pal/day as a criterion for rotary joint seal per-formance is of great advantage. This allows the rotary joint tooperate effectively within its range of optimum conditions, whileaffording a liberal safety factor on leakage loss of 3.0.

Pursuant to this recommendation, article 18 of amend3ment 2to paragraph 3.3.2.10, SOL-5296 was accordingly revised by, andgupon approval of, the Signal Corps.

In Page E4P 22 AV 2 R

I HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

i REPORT 10075 ADDfDU F

CALOUATION OF HORSEPWER RXQMR1DTO

ROTATE ANTENNA

I Assuming the antenna to be a flat plate of the dimenieonsshoum below, the horsepower may be oaloulated using the formula:

I H .i57 N2 p O'VD4 x 10-6

ihesre: N a rotational speed (rpm)

D = length of antenna (ft.)

j V - wind velocity (ft/lsec)

CD a drag coefficient

1 P - air density (slugs/fv)

For operating conditions:

V (max.) a 60 mph a 88 rt/seo

? (-650y) a o.oo032 slugs/ft

CD (noise) 0 0,53

T Hull ft,_H D . t.

D N-- rpm

EP a (.k47)(6) 2 (.O0312)(.53)(88)(4C# x 1o"6

I 1SP a 6.15;

The azimuth drive efficiency In assuMed to be 85"

then HP - 6 = 7.24.85;

Using next higher standard alses HP n 7,5 HP

In Page F1

P 22 AV A R

HAZELTINE- ELECTRONICS DIVISIONHAZELTINE CORPORATION

i REPORT 10075 Addendum F

I Derivatio of Wind Torque Bquation

(a) Wind Velocity Distribution:A flat plate rotating about its center has a relativewind velocity distribution as shown below:

V

f /••voso# +

I where: 0 - rotational speed of plate (radians/see)

V - wind velocity (ft/see)

0 a angle of incidence of wind from perpendioular(O)

I lR - radius of plate (ft.)

Left sides wind aids rotation (negative torque)

VL - V 00o 0 - Wr

Right side: wind inhibits rotationg effects are additive

Q VR - V o os a + or

Arsea:

Am RdA n H dr

I dr

In Page P2

P 32 AV * R

I1 HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

REPORT 10075 Addendum F

I (b) Torque MT):

T r wheretr : elemental radius

drag force on plateI Drag force:

F - 1/2 CD AV2

j where: C - drag coefficient

e w air density (slugs/ft?)

i A - area of plate (ft,2)

V - wind velocity (ft/sec)

T - 1/2e CD AV2 r

Left side: VL V cos 0 - W A B dr0

TLU =-1/2 a D (RH dr) (V cos 0 - ur)2 (r)

Right sides VR= V cosQ +TR =1/2 CD (R Kd') (Voos c + wr)2( )

0

Total torque: T - TL(-) + TRC+) = TR - TL

T n 1/2 CD (0R dr)(r) LVoos - (V coo. G-)2]

I T 1/2 DoD s H dr)(r) (4 coo,0 Q)

T a e CD H V 00" (aS r2 dr0

II n Page P3

P 22 AV 2 R

HAZELTINE ELECTRONICS DIVISIONREPORT 1HAZELTINE CORPORATIONREPOR 07• Addendunm F

Assume wind acting perpendicular to plate:

Angle of Incidence Q = 0

Cos Q a Cos 00 1

Substituting:

R m E (D = total length)2

x,11 14060 (N = rpm)

T- 2.4 N f O vc x 10-3

(W) Horsepower

HP - 2 Tr NT Substituting for T33,000

S= .di$7 N2 C D VD4 x 1o-6

In Page F4.P 22 AV A R


REPORT 10075

.I ADDENDUM G

I GEAR CALCULATIONS

1e AZIMUTH DRIVE GEAR DESIGN DATA SUMMARY AND CALCULATIONS

Limit MOS.Gear pace Beam Dynamic Load forPig. P.D. No. Width Strength Load Wear WbG1 D.P. in Teoth in. Wb(lbs.) Wd(lbe.) Ww(lbs.) R.P.M. Wd

SA 32.0 160 2.50 19,220 8200 9850 6.1* 2.35B 5 4.0 20 2.75 12,750 8200 9850 49 1.56

12.5 100 2.00 7,810 2922 3120 49 2.672.50 20 2.25 5,610 2922 3120 245 1.92

R 10 9.1. 91 1.50 4,610 1760 1940 245 2.52

I F 10 2.6 26 1.75 3,630 1760 1940 862.5 2.06G 16 5.0 80 1.25 20365 1470 1520 862.5 1.61H 16 2. '40 .1.50 2,130 1470 1520 1725 1.45

*The output speed of 6.1 RPM is a result of the choice ofg ear ratios. Although the nominal specified output Is

.0 RPM, the design speed of 6.1 RPM is within the require-innts of the design specification.

I AZIMUTH DRIVE GEAR CALCULATIONS

The design of the gear drive system Is based on the followingpa ramseters:

S~Drive motor to be 7.5 H.P. at 1725 RPH, stall H.P. 15(Ref: Di•ve motor calculations)

All gears to be 200 P.A. Spur, for maximum load oapacityS~at minimum oost.

All pars except gear "A" to be made of SAE 4140 alloyI ~steels heat treated and surface hardened as showin L

table above.

Gear "A" to be made of SAR 8660.

I In Page GlP 22 AV 2. R

HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATIONENRPORT l0072 Addendum G

Tooth beam strength to be based on stall (maximum) torque ofthe drive motor,

Dynamic load and limit wear load to be based on l5O percent(approximately) of rated H.P.

Pace widths to be approximately 5 times the circular pitch ofthe gear, (Ref: Maohineryls Handbook.) Gear "B" will be crownshaved and shaft parallelism will be closely controlled to Insure

full tooth meting.

All gears to be Olans 3 comreroial in order to obtain the re-quired precision at minimum cost*

Overall gear reduction is 287.5:1

sae DYIAMIC LOAD CALCULATIONSi (MAXIMUM OPERATING LOADS)

(1) Dynamic load calculations are based on the followingformula. (RefS Manual of gear design-1. Buckingham.)

(2) Gear designations an per figure 01 and table GI.

W- +0 V(PC+W),o V + PC+

Where: V - Pitch line velocity in F.P.M. -

ir x PF.D. x R.P.M.12

P n Pase width of gear in inches

C a Deformation factor (A constant based on gearaccuracy, tooth form and modulus of elasticity.)(From chart In Buokingbau.)

W a Total applied load = 33.000 x H.P.V

I

In Page 02

P22 AV 2 R


REPORT 10075 Addendum G

GEARS A and B

SW 7.9 x 103 lbs.V a 50.3 F.P.M.F a 2,5 In.C = 1660

Wd a 09 v(PC+W)

So05 x 5o.3(2.9- x 166o + 7.9 x 103) + 7.9 103S.0 x 50.3 + V2.5 x_1660 + 7.9 x 103

a 8.2 x Io3 lb..OUARSO nd,-D

W - 214.60 lbs.V a 161 F.PoM,F " 2.0 in,

C - 1660

.o0 x 161(2.0 x 1660 + &.6 x 102)

.05 x 161 + V2.0 x 1660 + 2I4.6 o2 x 102

1Wd 2922 lbs.

GEARS and F

VW 680 lbs.v 5 %83 F.P.I.F 1.5 In.c 166o

.a V (•' ,,÷ wWd ".05 v +vro w V

In Page 03P 92 AV 2 R


REPORT 10075 Addendius G

0 .5O x 583 (1.S x 1660 + 680) +680.05 x •83 + V- x 1660 + 680Wd 1760 Tha.

GEARS 0 and ee

W a 350 ltb.

V a 1130 ?.P..M.

IF a 1.0 In,C a 1660

I N .05v(FPO+W) +

j -. 05 x 1130(1.0 x 1660 + 350)

.05 x 1130 + V1.0 x 1660 + 350

1 Wd 1470 lbs.

I b. BEAM STRENGTH CALCULATION (MAXIMUM ALLOWABLE TOOTH LOAD)

Beam strength calculations are based on the Lewis Equation

Wb =StP F Y

WhereSt - Safe static bending stress of Sear material

P = Circular pitch ".

F = Face width

Y = Tooth form factor (obtained by considering thegear tooth as a beam# fixed at one end andloaded at the other) (Refs Manual of geardesign-2 Buckingham.)

In Page G4P 92 AV 2 R



REPORT 10075 ADDENDUM G

GEAR A st P F YWheres St a 70m000 lba/In. 2 Wb = 7 x 104 x .628 x 2.5 x .175

P a .628 in.F u 2o5 In. Wb = 19.22 x 103 lba,Y w .175

GBAR B Wb 0 St p p yWheres St , 7 0D0 0 0 lbs/in. 2 Wb a 7 x 1o4 x .628 x 2.5 x .116

P = .628 in.F a 2.5 in. wb w 12.75 x 0o3 lbs.Y - .116

GEAR O Wb - St P F YWhere.: 5t - 70,000 lbs/in. 2 Wb n 7 x 104. x .393 x 2 x .142

P = .393 in.F 2.0 in. Wb L8.1x 102 lbs,Y .142

GEAR D Wb = St P P y

Where: St - 70,000 lbs/in. 2 Wb a 7 x ICA x .393 x 2 x .102P # .393 In.F 2.0 in. Wb= .Jz10 2 =b.

Y 1 .102

GEAR E Wb = St P F Y

Where: St n 70,000 lbs/In. 2 Wb 0 7 x 10" X .314 x 1.5 x .140P a .314 lm. Wb = L6.2 x 102,1be.P = 1.5 In.2 = .140

In ^ • Page G5



G EARF Wb a St P FY

Where: St U 70MOO0 lbs/In.2 Wb = 7 x 104 x .314 x 1,5 x .110P a .314j in.

=1.5 i. Wb ,63 1 lbs.I Y * .110

GEAR 0 Wb = St P F Y

Where: St 0 70,000 lbs/,n, 2 Wb a 7 x 104 x .196 x 1,25 x ,138P a .196 in.P a 1.25 in. Wb - 23.65 102 lbs.Y . 138

GEARX Wb-StPFYWhere: St - 70,000 lbs/in. 2 Wb - 7 x 104 x .196 x 1.25 x .124

P = 196 in.F a 1.25 In. Wb a 21.3 x 02 lbs,Y W .124

o. MARGIN OF SAFBTY

Assuming pulsating load conditions: Wb • 1.35Wd

Which means that for peroply designed gears, the tooth beamstrength should be equal to or greater than 1.3ý times theoperating load. (Reft Manual of gear desIgn-E. Buckingham.)

The following Is a tabulation of the M.S. of the gears:

OGAR MS -WbWd

A 19.22 x 10 w 2.35

8.2 x 102

8.2 x io3

| 78,12 102 . 2.6729.22 x 102

D .1.9229.22 x 102I

7 InPage 06

p 2. AV 2 R

HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATIONREPOR"' 1007% Addendum G

GEAR WS= bWd

4 6.2_ x. 102

17.6 x 102 - 2°02

P 36.3 x 102 , 2.0617.6 x 102

G 23.6• xo2 .1.61

147.? x 102

H 21,3 x 10214.7 x 102

d. LMIIT LOAD FOR WEAR

(1) Limit load for wear Is based on the formula: W DFKQ(Ret: Manual of gear design-E. Buckingham,)

Where: D a Pitch diameter, pinion, inchesP w Face width inches 2

K - Load-stress factor - _w2 sin-< (I/. +1.4 \,E 'E22

Where: Sw a Surface endurance limit

`< a Pressure angle

E - Modulus of elasticity of pinion and gear

Q = Tooth ratio L 2L (spur gear); 2N (inte-al gear)

N+n N-n

Where: N = No. of teeth in gear

n a No. of teeth in pinion

(2) For acceptable gears Ww > Wd

To provide oontinuous service without appreciable wear.



REPORT 1O075 Addendum G

jG•ARS A and B w. a DFIQ

Where: D - 4.0 In. Wv,1 4,.0 x 2.5 x 430 x 2.29F a 2. In,K = 4 30 ww = 9.8S' x 1o3 .> wA 8.2 x lo3

Q = 2.29

GEARS C and D Ww w DFKQ

1 Whores D a 2.5 In. Ww = 2.5 x 2.0 x 375 x 1.67F - 2.0 In.

I aC 375 Ww a -. 2 x 102 >WA w -29.2 x 102

Q w 1.67

GEARS B and F Ww a DFKQ

Wheres D 2.6 in. Ww a 2.6 x 1.5 x 318 x 1.56F * 1.5 In.X = 318 ww = 19.4 x 102>.WA - 17.6 x 102

Q w 1.56

GEARS o and H ww w DFQ

jWhere: D * 2.5 In. Ww = 2.5 x 1.25 x 366 x 1.33

F 1 125 in.K - 366 Ww = 15.2 x 102 >Wn = 14.7 x I02

Q * 1.33

IIII

I

In Page G8P 22 AV 2g R



TABLE G1, GEAR MATERIAL HARNDESS DATASURFACE

GEAR HEAT TREAT HARDNESS

A See report on main bearing

SB •Re 32-34 Re 57-59

C Re 32-34 Re 2.-44

D R 0 32-A Re 46-48

IE Ho 32-3k Re 36-40

F o 32-34 Re

j G Re 32-34 Re 4-42

H fi 32-34 R 4-4

e. GEAR LIFE EXPECTANCY

The calcalation of the life expectancy of the gears Is basedon the statement in "The Manual of Gear Design," by E. Buckingham,that the life of a gear is equal to the inverse proportion of the

Sload raised to the 10 power. Using load-stress factor "K" of 430

for gears *A" and "1B (the lowest life expectancy gears), andbasing the life on 100 x 106 cycles, a maximum compressive stress,Set of 163,000 is obtained from the chart in the referenced text.The actual compressive stress is found from:

So 35W L1 +1/ 1 2

1R, R2

Where: W a Tooth loadR, = Pitch radius of gear x Sin Pressure Angle

R2 = Pitch radius o f pinion x Sin Pressure AngleL = Face width

E1 and E2 - Modulus of elasticity of gear and pinion

ln Page G9P 22 AV 2 R



Therefore: S0 u 18I,600 lbso/in. 2

The life factor then becomes: 10FL = 16".000 3 .66

184,6oo

( To find the life expectancy at the actual load:

L = .66 x I00,000,000 cycles

I- 66 x 106 cycles

or L 66 x 10 6

RPM x 60

I L - 10.000 hours

Since gears "A" and "B" have the smallest life expectancy,i calculation for only those gears where shown.

2. SYNMHRO DRIVE BACKLASH CALCULATIONS(Refer to Figure 02)

GEAR

DATA J L M N K R

I No. Teeth 396 66 128 32 32 192

Die. Pitch 20 20 32 32 32 32

Pressure Ang. 200 200 14-l/20 14-1/20 14-1/20 14-1/20

I Pitch Die. 19,800[ 3,300 4,000 1,000 1,000 6,000

To find the backlash at the individual meshes we have:

1Backlash - C Van Keuren(inches) 1/2 COT % pg. 116

I orBacklash - 2 (A C) TAN(inches)

I

in Page GIOP 22 AV 2 R



To find lost motion of the driving Sear with the synchroastationary we have:

I21 4 1LL. D. Martin

R2Y D2 4R4 Machine DesignMay, l953(Radians)

Nomenolature

B - Backlash R - Testing Radius

C = Center = Pressure Angle

D = Testing Diameter 0 a Arc of Lost Motion

Lost Motion of driving gear from 1:1 aynchro:

BJL m 2(AC) TAN 0 Tol. on dist.* .0142(.0207)(.364) = .0151" Comp error (preo.el 1) , .001

Shaft tol. - .0005Bearing tol. = .0002Distortion due toload on large brg , .001.C - .0207

BKR - 2(.0035)(.258) - .0018" Tel on dist.* - .0018Comp. error (preo.ol.l) = .001Shaft tole a .0005Bearing tol. a .0002

tR Dc + . 0035

.0119 + .00 - 13 Radians

-.0134 x 3438 - 146.07 Minutes

19JR t 23 minutes

*Toleranr on ý distance due to maohining tolerances on bullgear bearing, upper and lower bearing support castings andlocation of synohro gear box.

In Page G1I

P 22 AV 2R



Lost motion of driving gear from 24:1 synohro:

BTL = .0151

BW W .0018 (same as BKR)

QJN a(BMN)DL + BJL

IW 0018 1L,..+.,01512 4 9.9

G0(.09) .825 + .0015

.0007 + .0015 = .0022 radians

.0022 x 31438 - 7.56 minutes

* 4 minutes

3. SUMMARY OF GEAR SHAFT BEARING DESIGN DATA AND AZIMUTH BEARINGLOAD CALCULATIONS

a. Summary of Gear Shaft Bearing Design Data

BRG, ACTUAL LOADIDENT. BEARING ACTUAL CORRECTED RATEDFIG.G3 NUMBER LOAD FOR LIFE & SPEED LOAD

I 499503 350 at 378 lb. 440 lb.1725 RPM

II 499503 111 at 120 lb. 4140 lb.1725 RPM

II1 43305 16.1 at 17.5 lb. 1111 lb.825 RPM

IV 499605 412 at e445 lb. 1110 lb,862,5 RPM

V 499508 113 at 1556 lb. 2150 lb.245 RPM

VI *R-345-LL 4I030 at 6860 lb. 9450 lb.245 RPM

VII *R-365-LL 1I000at 12,750 lb. 22,800 lb.48 RPM

VIII *R-365-RR 20,030 at 19,65o lb. 26,600 lb.1_48 _RPM II I

In NOTZS: 1. All bearings "New Departure" except those marked *,1122 AV 2 A 2., *Denotes "Norma-Hoffman" bearings. Page 012

P 22 Av 2.Pg I

Ii HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

i REPORT 10075 Addendum G

i NOTES (Cont'd)

3. a. New Departure bearings corrected for life andspeed by formuls R - Re x L, whereRe a corrected loadRe - actual loadL = correction faotor (N.D. Handbook Pg. 10)

b. Noma-Hoffman bearings corrected for 1lie andspeed by formula R a Ra x L x S where

-R corrected ioaaRa * actual loadL - life factor (Ref. Norma-Hoffman Catalog

I S speed faotor Pg. 126)

b, AZIMUTH BEARING LOADS

Bearing load caloulations are based on transmission of 15 H.PoSince only a negoligible thrust load (the weight of the gears andshafts) exists the load on the bearings is a function of theresultant of the separation and tangential forces developed bythe gears, and the distance of that resultant from the supportingbearings of a given shaft. See figure G4 and G0.

TerminologyQ n Torque transmitted a H°P* x 6302•

RPM

P = Tangential force - Pitch Radius

S a Separation force m P x TAN OC ( whereK - toothpressure angle)

L - Resultant forces - Vr ÷ S2

1 (1) Bearing and gear identifieation is shown in figure G03,

(2) Roman numeral subscripts to P and 8 Indicate bearingreactions.

(3) Arabio numeral subscripts to Q, P and S Indicate gearmesh number*I

I

In Page 013P 2 AV 2 R




BEARING I

15 x 63025 58 PI 438 x Z4.9 3 3 31725 6.50P- 5'•= L. 438 sI 1= A9 k, -. 121

1.25 6.50

Si 438 x .364 59 LI 4333)2 + (121)2

-L 350 Lbs.

j ~BEARING nIPli k38 x 1.56 0 1 + L2

S6L50 LI I Lb 3

= 159 x 1.56. 38 LII= 1O I b.I6.50

NOTE: Sub-subscripts denote gear mesh, e.g.,P1ii is

the tangential force reaction of the first meshon Bearing III.

BEARING Ill N.B. in calculating LIII - and P1111are shown negative since they are acting in adirection opposed to SIII2 and PIII2

Q2 = 1:x;6302 - 1090 Pin, = 3 x 323863 5.25

P2 = 1.32-0= 838 S 1 .a 159 x 3.87 = 1171."• 3 8 1II 5.25

S2 = 838 x .36k 0 303 P3II2 a 8 = 3382 5.25

SLZ V523'- 338)2 + (125 - 117)2S sIll W 3,03 x 2,12 - 125

2 5.25

L111 - 16.1 Lb.

In Page G14




BEARING IV

p v, = 4• Bx 1.38 . 1 1 PV a 838.x 3.13 a 0oo5.25 2 52

S159 x 1.3842 87 2 = 303 x-3.13 ,181L y.o5.25 _ 115)2 + (181 4 5.25'

t ~ ~~~LIVI = V (50°"0 5'2+(ZZ- )

LIV a L12 Lbs.

BEARING V

NOTE: In the 8cloulatiom of loads on Bearings V and VIthe angular displacement of the shafts #2 and #3was ecmeldered by using the components of theforces.

Q3 1 x 63025 = 3860245

P3 a 80 = 309531.2%;

S3 = 3095 x .364 a 1126

Pv " 838 x 12 +3095 x .358 x 2.25 +1126 x .93h. x 2.2510.5 -0,5 10.2

Pv a 1421

8-v 303 x12 +1126 x358 x2.25 +3095 x .293hx 2.25lo.10 10.5 10,

sv - -185

Lv = Vt(42i)2 + (.185)2Ly a 110.5 Lbs.

I on Page 015P92 AV 2R



BEARING VISPvl " 838 • A 1+ 3-09. x ,35qz 12,75..& 1126 x ,93k x 12.75

10.5 10.5 10.5

I PV = 2740Svzt , Inx . + 1126 x .350 x 12.75. + 3095 x #93L X- 12,.25

SVi = -2957

L a V(2740)2 + (-2957)9SL " 4030 Lbs.

BEARING VII43 La

q _3 ,9 15 x 63025 , 19720 pVxx 3095 x 6.5 ,,S48 3 4

P4 a 19720 = 9860 sv*l a 1126 x 6.5 w 1830

2 9 4

84 w 9860 x .364 -3590 V 9860 x 2.94 a 7250P14 4.

SVII 4 3590 x 2.9 a. 26404

tvif = (5020 + 725o)2 + (1830 + 2640)2

rLVII = 13.000 zLbs,

BWARIN VII

PVII"°•w3 095 x 2 -5 1932:3 4 .

4.8Vii=11 26 - 2.5 705

LI

P22 APage G16P 2•2 AV 2 R


REPORT L0075 Addendum G

BEARING VIII (Cont'd)* 9860 x 6.9,! 17,100

S~4

3S90 X 6.914. 6230

Lv111 0(1932 + 17100 )2 + (705 + 6230 )2

LIll " 20.030 Lba.

f lj.. AZIMUTH GEAR SHAPTS

a. Genexal

I All shaft caloulations are based on the shafts being madefrom SeA.B. 14140 alloy steel)heat treated to 150#000 p.o.*,

Allowable torsional shear stress Is taken to be 18 percentof the U.T.S. (see above). (Ref. Marks Handbook.)

g Shaft designations are shown In figure GI.

Minimum shaft diameter calculations are found by using thei formula:

Dm" ~ M )2 + (Kt T)2 (Ref. Marks Handbook)

%tere: so - shear stress 18% U.T.S. - .18 x l1,000 - 27,000 p.s.-.

iK - shook and fatique factor 3 (Assuming worst load-

Kt - ahook and fatigue factor a 3 Ing caciditions)

M - maximum bending moment (see derivation below)

The value of M for shafts #1 and #2 Is obtained fromI the beam formula for a beam supported at the ends witha conaentrated load at any point,

L

In Page G17P22 AV 2 R

"HAZELTINE ELECTRONICS DIVISION

HAZELTINE CORPORATIONREPOR~T 1007• Addendum 0

b. Shaft No. I

P a 159 lbs. (S, of bear3ng load calculations)a a 1,56

M - 1 1.56 x k.9

6.0

T 548 (Q of gearing load calculations)

-D a 8.9 x 10-5 V3 x 200)2 + (3 x 8)2

D1 .7i!5 in.

o. Shaft No, 2

N.B.: The total bending moment on shaft No. 2 is thealgebraic sum of the moments of S, and S2 which are acting inopposite directions.

P1 - 159 lbs. (81 of bearing loads)

,a1•92x 1.3_8 X3.871 - i 5.~x525

a - 1.38 in.a : I ob 3.17Inn: H 1m61 In, b.,L a .2

P11 a 303 Ibs. (82 of bearing load calculations)

d a 2.12 In.b -3.,13 in.L 5.2 in. 303 x 2.12 x 3.13

52 .2

X2 -381 In. lb.

MTOT M N2 - M1

a 381 " 161

MT0T - 220 in. lb.


"IHAZELTINE ELECTRONICS DIVISION


REPORT 10075 Addendum 0

i T - 1090 (Q2 of bearing load calculations)

SD2" 3•8.9 x10"-5 \3 x 220) 2 + (3 x1090)2

j D2 - ind. Shaft .3

N.E.: The totalbending moment on Shaft No. 3 is thealgebraic sun of the moments of S2 and Sj which are acting inopposite directions. 7he bending momenta are equal to the force

5 8 times its distance from its sipporting bearing.

P1 a 303 lbs. (S2 of bearing loads)

I NL1 a 1,5 in,iM1 - PILl a 303 x 1.5

M1 - 455 In. lb.

P2 - 1126 lbs. (S3 of bearing loads)

L2 - 2.25 In.

M2 " P2L2 - 1126 x 2.25

M2 - 2525 in. lbs.

TO = M2 - M a 2525 - 455

T - 3860 (Q3 of bearing loads)

}F- -X1- 03~g O'/(x 207'0')2 + (3 x 3860)2

D3 " 1 j

I e. Shaft No. L

N.EB: Simne the physical arrangement of shaft No. 4 isthe same as shaft No. 3, calculation of the total bending momenton shaft go. 4 follows that of Shaft No. 3.

P1 - 850 lbs. (S3 of bearing loads)

LI a 2.88 in.

In Page G19

P22 AV 2 R



MI = PIL, - 1126 x 2.88

-M, 3240 in. lb.

P2 = 3590 lbs. (S4 of bearing loads)

L2 w 2.94 in.

""2 P2a = 3590 x 2.94.

I m2 . 10,55o in. lbs.

MTOT M2• M-1 = 10,550 - 3240

MTOT - 7310 In. lbs.T = 19,720 (Q4 of bearing loads)

F 18. 9 4 0(3 31x 0) (ý3x 1ý9.72 x10)114-~~~ ~ ~ 102)23,731x 02

D4 .2.28 In.

f. Conclusion

The foregoing shaft diameters are minimum reqjuiements.Actual shaft diameters will be affected by the bore size of thesupporting bearings requiredt but will always be equal to orgreater than the calculated minima.

The following safety factors indioate the ratio of theallowable working stress to the assumed working stress of theactual shafts.

S D3 actualD3 calculated

Shaft No. 1 S.F. , (.937)3 , 2j2..(.715)3

Shaft No. 2 S.F. a (1,2913 a 3(. 8•6 ) 3

Shaft No. 3 S.F. = (1773)3

S.. (2.g3)3Shaft No. s.. - (2.8)3i 12"28)3

ln Page G20P 22 AV 2 R



III

-- -SGEAR "H "

GEAR"'8"

\t S2GEA R"G"

pp 3

Figuz'e GI. Azimuth Dzve GeaRing

Page Ge21

P22 AV 2 R



II

IN

ICOPIGCULN CAM POSITION

INDICATORISWITCH

Page G22

P 22 AV 2 R



AdII

II

URG. NO. M" BO NO. M

1

I Figure G3. Typical Azimuth Bearing Load Analysis

I

MP

T PPge A23

P 22 AV 2 R



ILI

b

j L+ b

LOAD ON BRG. NO. I :--a+b

LOAD ON SRG. NO. X: L-aa+b

iFigure G4. Basic Bearing Load Analysis

iz*"1

U)

St SIN 6

P2

Figure G5. Typical Force Analysis of Angularly Displaced Shafts

Page G24

P 22. AV 2 R


Report 10075

ADDENDUM H

WIND FORCE ON REFLECTOR ASSEMBLY

The drag force produced when relative motion exists between

a fluid and a solid body is described by the formula:

Fd = i9Cd A V2

where:

Fd = drag force (Ibs)

I A = projected area of solid body (ft 2 )

V = velocity of relative motion (ft/sec)

Od = drag coefficient (dimensionless quantity dependent uponconfiguration and surface conditions of solid body)

I ?= density of fluid (slugs/ft3, dependent upon temperatureand pressure conditions of the fluid)

I For Air at Sea Level

where:

I Ta = absolute temperature (degrees rankine)

Pc = standard air pressure at sea level = 29.92" Hg

1g = 32.2 ft/sec2

at_- F1 Ta = 395°R

• l2..)(2 9.92) .00312 slugs/ft 3

Survival Conditions

Case I:

I V = 90 mph = 132 ft/sec

II avs Page HI

P 22 AV 2 R


Report 10075 Addendum H

I * Cd (5/8" squarex meshp without ice) = 053

A = 364 ft 2

= .00312 slugs/ft3

I Fd = 1 (.00312)(0.53)(364.)(132)2 = 5340 lbs.

I * Derived from wind tunnel tests, applies to this size squarexmash only,

I Case II0

V - 40 mph a 58.6 ft/seo

I Cd = (antenna iced, approximates flat plate) a 1.0

A = 364 ft 2

e a .00312 slugs/ft 3

Fd = 1 (.00312)(1.0) (364)(58.6)2 - 1950 lbs.

Obviously, the most severe wind loading conditions occurwhen the wind velocity is 90 mph, the reflector being free of ice.The force produced is 5340 lbs., equivalent to a uniform staticload of 14.7 lbs/sq. ft.

I

II

IIIi avs Page H2

P22 AV 2 R


REPORT 10075 Addendum I

'1 ADDENDUM I

STATIC LOAD AND DEFLECTOR TESTS

Test Procedure

The reflector, reflector support and feed support were suspendedfrom a heavy steel frame, with the reflectorts vertex pointed towardsthe zenith. Male and female self-reading aluminum gauges were at-tached to the reflector and reflector support, to record deflectionsat any loading condition (see figure II). A representative sample ofconcrete blocks was weighed on a calibrated scale and found to be 61pounds per block.

A summation of the moments in comparing the load on the reflectorsupport and pedestal bolting arrangement for, first, the reflectorIn its vertical location and, secondly, the reflector in its testlocation shows that 800 lbs of the antenna panel sections must beincluded as part of the effective loading to obtain valid results.In addition, 160 lbs. of 1/4-inch masonite was used to protect thescreen surface of the reflector.

Concrete blocks simulated the load and were oriented so bothhalves of the reflector were symmetrical, and distributed to obtainuniform loading.

Test Results

Test results showed that the antenna easily surpasses its re-ulrements. In interpreting the results of the deflection readingstables Il and 12), It must be remembered that the basic calibration

was established with 800 lbs. of panels and 160 lbs. of masonite onthe structure. This represents a distributed load of 960 lbs/365ft. for 2.63 psf. This is, therefore, the zero datum for alldeflection readings.

The Operation Average Net Deflection (table 13) uses the ver-tex location after deflection, as a datum to show the surfacetolerance. Where there are symmetrical readings, these have beenaveraged: e.g., 1-IA, 2-2A, 3-3A, 5-7.

The Suriival Average Net Deflection (table 14) uses the "WBrace" (i.e., 5 & 7) pick-up points as a datum to show the actualmovement of the reflector itself with respect to the support struc-ture. It should be noted that there is basically no deflection atthe vertex. This was anticipated, for there is a negative bendingmoment and deflection in the central section. This is counter-balanced by the force of the local distributed loadings; therefore,

In Page II

P S2 AM IR



little or no deflection occurs. These values have again been averagedas discussed in the previous paragraph.

Finally, it should be noted that there is an angular deflection3of the beam, in addition to the surface tolerance deflection. This

angular movement can be approximated by taking the difference of the4 and 4A rods = 0.0013/132 inches = Tan 0 = 0.00227; therefore =00 -08t for the operational loading.

TABLE II, FIELD DATA DEFLECTION READINGS

INITIAL OPERATIONAL SURVIVAL CLIMAX OPERATIONAL FINALLOCATION READING READING READING READING READING READING

1A 0.l" 0.6" 1.0" 1.25" 0.7" 0.25"2A 0.0" 0.35" 0.4" 0.45" 0.5" 0.05"7A1. 00." 0.75" 0.9" 0.45" 0.1"

0A 0.1" 0.I 0.05" 1.45" 0.7" 0.2"

4 0.1" 0.1" 0.4" 0.45" 0.15" 0.0"6 0.1" 0.3" 0.1" 0.2" 0.3" 0.15"4A 0.1" 0.4" 192" 1.4" 0.5" 0.0"2 0.0"1 0.2".45" 0 o.4" 0.25" 0.05"5 0.1" 0.45" 0.75" 0.9" 0,5" 0.15"3 0.1" 0.55" 1.05" 1,2" 0.7" 0.25"1 0.2" 0. 55" 0. 85" 1.0" 10.65" 0.2"

TABLE 12. TEST DATA DEFLECTION READINGS

TOTAL TOTAL DEFLECTION DEFLECTIONNUMBER LOAD LBS. P.S.F. LOAD LBS. P.S.F.

1) InitalReading 960 2.63 0 0

2) OperationalReadings 3220 8.82 2260 6.19

3) SurvivalReadings 5380 14.7 4420 12.1

4) climaxReadings 5810 15.9 4850 13.3

5) Additional noLoadings 6260 17.15 readings

6) OperationalReading #2 3220 8.82 2260 6.19

7) FinalRetadinga 960 2.63 0

ln Paes 12P 22 AM 2R



TABLE 13. OPERATION AVERAGE NET DEFLECTION

GROSS VERTEXOPERATIONAL INITIAL DEFLEC- (BASE) NET AVE NET

LOCATION READING READING TION DEFLECTION DEFLECTION DEFLECTION

IA 0.6 0.1 0.5 0.2 0.3 0.222A 0.35 0.0 0.35 0.2 0.15 0.077 0.4 0.1 0.30 0.2 0.2 0.173A 0.6 0.1 0.5 0.2 0.3 0.274 0o.1 0.1 0.0 0.2 -0.2 -0.2

6 0.3 o.' 0.2 0.2 0.0 0.04A 0.4 0.1 0.3 0.2 0.1 0.12 0.2 0,0 0.2 0.2 0.0 0,075 0.45 0.1 0.35 0.2 0.15 0.173 0.55 0.1 0.45 0.2 0.25 0.27

1 0.55 0.2 0.35 0.2 0.15 0.22

The surface tolerance is a function of the total deflection ofany point less the vertex deflection of 0.2 inches. The left sideof the reflector deflected more than the right side; therefore, theaverage of corresponding points has been taken as a true reading.

TABLE 14. SURVIVAL AVERAGE NET DEFLECTION

GROSS "W" BRACESURVIVAL INITIAL DEFLEC- (BASE) NET AVE NET

LOCATION READING READING TION DEFLECTION DEFLECTION DEFLECTION

IA 1.25 0.1 1.15 0.8" 0.35 0.172A 0.45 0.0 0.45 0.8" 0.35 -0.357 0.9 0.1 0.80 0.8" 0 03A 1.4 0.1 1.35 0.8" 0.55 0.424 04, 0.1 0.35 0.811 -o.95 -0.45

6 0.2 0.1 011 0.8" -0.70 -0.704A 1.4 0'l 1.3 0.8 0.50 0.502 0.45 0.0 0.45 0.8" -0.35 -0.355 0.9 0.1 0.8 0.8" 0 03 1.2 0.1 1.1 0.8" 0.30 0.42

1 1.0 0,2 0.8 0.8" 0 0.17

The surface tolerance is a function of the total deflection ofany point, less the base deflection at the outboard "W Brace" pickup points. The left side of the reflector deflected more than theright side; therefore, the average of corresponding points has beentaken as a true reading.

In Page 13

P9R AM 2 R


I REPORT 10075 Addendum I

I

1 .4A

I

2 2A

4

FiSgure II. Location of Deflection Gauges

Page 14

P 22 AV 2 R


REPORT 10075 Addendum J

ADDENDUM J

MOISTURE RESISTANCE TEST

Test Procedure

(a) Dry at 1300 ± 50F for 24 hours.

(b) Conditioned at 770 ± 50F and 40 to 50% relative humidity for24 hours.

(W) Pedestal performance measurements were taken as described inparagraphs 3.3.2.2 and 3.3.2.5 of the Technical Requirements. Thefollowing cycle was performed five times. Temperature tolerance wasmaintained at ±50F. Relative humidity was maintained between 90 and98%.

(d) The temperature started at 86*F and was increased to 149*F infour hours at a rate of not less than 15 0 F per hour.

(e) The temperature was maintained at 149'F for eight hours.

(f) The temperature was returned to 86*F in four hours at a rate ofnot less than 150 F per hour.

(g) The temperature was maintained at 86 0 F for 21 hours. Pedestalperformance measurements were taken during this step between theeighth and 12th hours.

(h) The temperature was lowered to 68°F in one hour.

(I) The temperature remained 68OF for four hours.

QJ) The temperature was raised to 86 0 F in one hour.

(Note: The change in temperature from step (i) to step (J) was notless than 1800F.)

(k) The temperature was maintained at 86 0 F for five hours afterwhich pedestal performance measurements were made. (Note: Endof cycle.)

(I) The pedestal was conditioned for 24 hours at 770 + 5± F and40 - 60% relative humidity after which pedestal performance measure-ments were made.

Tea 't Results

The data sheet on the following page provides the test resultsusing the procedure above.

In PAge Jl

IP 22 AM A R

II HAZELTIHr

1 ~REMUT 10075

I Obser~ved ,.Data DATA

ICONDITIONING FIRtT CYCLE SWd0ND C1

ISTEP (a) STEP U) STEPDO) -TP aOperating Voltage----. . 120 126 126 126V2 120 126 3.26 126V3 120 126 126 126

1 Starting Current-amps-I 1 87 88 82 " "j12 87 82 82 8313 87 82 86 86

STime to Attain Speed inst. Inste. Inst. Inst.Operating Current-amps-I 1 6,o 8.2 8.0 8.1

12 7.0 8.7 8-4 8.413 6.5 8.7 8.4 8.2

, Power-watts -------- Wz 250 220 200 200; 200I. W 230 210 220 200

. 120 170 140 140PedestAl Speed.•.R 6.2 6.2 6.2 6.2

Thermocouple Readings-(deg,. UF OF

Position Chamber 80 90 86 870uter Casting 75 88 86 87Thermostat Well 75 88 86 87Inner Casting Level #1 75 88 86 87

Inner Casting Level #2 75 88 86 8?Rotary Joint-Floating NT, 75 88 86 87

Oil Filter-Top 75 88 86 87Beater 75 88 86 87Oil-On Dipstiak 75 88 86 87

Gear eNsh Oil Tube 75 88 86 87

In


Adendum J

DATA SHMZJs MOISTMUE RESISTANT TEST

FINALICCESECOND CYCLE THIRD CYCLE FOURTPH cCE FIFTH CYCLa CONDITIONING

ST h TP().TEP (k) STEP (9) STEP (k), STEP (g) STEP (a),~J L STEP (g)ST W STEP U))

126 126 126 126 126 126 126 126 126 126126 126 126 126 126 126 126 126 126 126126 126 126 126 126 126 126 126 126 126

82 -,5) 92 84 83 92 90 92 92 9082 83 92 84 83 92 90 92 92 9286 86 92 814 83 92 90 92 92 92

Inst. Inst. mast. Ist. Inst. inst. Inst. Inst. Inst. Is.

8.0 8.1 8.1 8.2 8.3 8.0 8.2 8.2 8.2 7.78.4 8.4 8.4 9.2 9.2 8.2 8,14 9.2 9.2 9.28.4 8.2 8.2 8.2 8.3 8.2 8.4 8.4 8.5 8.6

200 200 200 240 40 220 220 200 200 240220 200 220 160 160 200 202 220 202 190

0 1o40 140 140 1o40 260 120 120 140 140

6.2 6.2 6.2 6.2 6.2 6.25 6.2 6.2 6.2 6.2

86 87 86 88 87 100 87 90 88 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

86 87 86 88 85 90 85 90 86 78

42


REPORT 10075 Addendum K

ADDENDUM K

TEMPERATURE TESTS

Test Procedure

(a) The ambient temperature was set to 77' 1 3*F and the relativehumidity set to less than 75 percent. Pedestal performance testswere taken,

(b) The temperature was raised to 1630 ± 3'F for a period of fourhours. The relative humidity was uncontrolled.

j (o) The temperature was lowered to 153° ± 3*F and the relativehumidity remained uncontrolled. Pedestal performance tests weremade within 30 minutes of the time these conditions were met.

(d) The temperature was lowered to -680 ± 3°F for a period of 24hours with the relative humidity uncontrolled.

The results of the next 48 hours of the test are given in logform, Table Kl shows temperature readings taken during that intervalof time.

October 28, 1958

* 9:00 AM Heater off. Thermocouple readings as shown. Attemptedto start motor. Ammeter needle went off scale (100A)came back to approximately 90A for a second or two andthen fuse blew. Replaced fuse and tried to turn pedestalwith hand crank. Found immovable. Turned heater switchon. No heat as evidenced from No. 13 thermocouple read-Ing. Check of control box shouad voltage to be presentacross relay. Removed access door and contactor boxdoor to check voltage to relay and heater continuity.From this time on (approx. 10300) the above doors wereleft off. Heater trouble was traced to the relay beingstuck and It was shorted out.

* 1l:50 AM Heater turned on.

12:00 PM Turned slightly and with great difficulty by hand crank.

12:10 PM Tried to start and blew fuse.

2:00 PM Pedestal allowed to cool for over an hour. An investi-gation then indicated that the fuses being used in thecontactor box were not slow blow fuses. Since none were

In Page KI

P A AMA*

HAZELTINE ELECTRONICS DIVISION"HAZELTINE CORPORATION


* 2:00 PM available, steel slugs were substituted for the fuses.(oont'd) However 40A slow blow fuses were in series with the

line at the power box. It was decided to wait thefull 30 minutes after heaters were turned on.

* 3:45. PM Turned heater on.

* 3:55 PM Thermocouple readings taken to see if there was anyappreciable difference over the 12:00 noon figuresbecause of the slightly higher initial temperatures.The heater was then left on for 20 minutes more beforeattempting to start.

4:15 PM Attempted to start motor by holding start switch 5 to10 seconds. Ammeter needle went off scale, returnedand held at approximately 90A. No start.

j i025 PM Same as 4:15.

4130 PM Pedestal turned with hand crank. Effort expendedapproximately 1 -1/2 times that at room temperature.

0.35 PM Same as 015.

** 4145 PM Pedestal started to turn very slowly and came up tospeed in a few seconds. Ran for about 2-1/2 minuteswith oil flow indicating normal and then shut down.Tried to start again and pedestal came right up tospeed but shut down after about two minutes. Metersshowed momentary peak of 90A and then returned tonormal running current. Motor cut out traced to -10

I thermostat.

7S00 PM Th• pedestal was allowed to cool down before tryingagain.

* 10:05 PM No heat, pedestal started right up, oil flow indicatednormal, and motor was cut out approximately twominutes after start. Indications were that eitherthe oil level dropped below the thermostat exposingit to the cold air or, with the oil circulating, coldoil was being brought into contact with the thermostat.Another gallon of oil was added to the pedestal, butwith the same results. Left to soak overnight.

In Page K2

P A AM AR


REPORT. 10075 Addendum K

October 29, 1958

* 9:08 AM No heat, pedestal started right up, ran for a coupleof minutes and then was shut off. The motor controlthermostat was shorted out. Pedestal performancetests were made.

9:11 AM Heater turned on.

** 94O0 AM Minus 10 thermostat closed. Thermocouple No. 17 read680F. Number 12 read -130F.

* 9:55 AM Pedestal started. Number 17 read +850F. Pedestalstopped after two minutes. Number 17 read 35 to 400F.

10:10 AM Pedestal started. Number 17 read +91 0 F. Pedestalstopped after 3 minutes. Number 17 read +300F.

* 10:35 AM Pedestal started. Number 17 read +84 0 F. Pedestalstopped after 3-i/4 minutes. Number 17 read +300F.

* 10:55 AM Heater was shut off for about two minutes, during theperiod between this and the last reading. Pedestalstarted and ran for 3-1/2 minutes. Number 15 read.-490F reached a peak of +55 0F and dropped to 300F

when the motor shut down.

* 11:15 AM Ran 4 minutes. Number 15 started at -40 rose to +40then dropped to 28 as thermostat opened.

* 11:32 AM The pedestal was started and allowed to run until itshut down. Then after a one minute period, it wasstarted again and allowed to run until it was trippedby the thermostat. This procedure was continued for40 minutes with the pedestal being unable to rotatecontinuously for any great length of time. At thesame time, thermocouple readings were taken every fiveminutes.

* 12112 PM The thermostat was shorted and the pedestal allowed

to rotate during the lunch break.

* 1:44 PM Reading taken after lunch.

* 2:00 PM Last reading taken during this particular run.

* Temperature reading taken before start of test.

** Temperature reading taken after start of test.

1In Page K31*AMn*



(e) The temperature was raised to 770F ± 30F with relative humidityless than 75 per cent. Pedestal performance tests were performedwithin 30 minutes of the time that these conditions were reached.

Test Results

Table K2 tabulates the results of the temperature tests fromthe procedure above. Malfunctions found, and solutions providedare given in part d of Phase 3 in section 4.

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P 122AM A Nt

HAZELTINE ELECTRONICS DIVISIONREPORT 10075 HAZELTINE CORPORATION Addendum K

+~C~ +CI(~ +H+ -+I+

wW 000000%001. NC0C.%00 M

+ +

N"

÷o 0 ÷ .Q

i '•~9 i'•i' ••-i'

§J O v I T +I . .- I .I +++

N I It3 §or A- l NAH H I

(V ~ ~ c~ Co - ,T 1A0 M M t-gL~

U+

jn P~ge KSP , AM t 0.




TABLE K2. TEMPERATURE TEST DATA SMEET

Observed Data

STEP (a) (c) (d) (a)

TIME 10/24/58 //125158 10/29/58 10/30/582:30pm 8:05am 9208am 9:20am

Operating Voltage-...-V 1 126 126 115 120v126 126 115 120V3 126 126 115 120

Starting Current-amps-1 1 90 92 92 8612 92 92 92 881 13 92 92 92 86

Time to Attain Speed Inst. Inst. Inst. Inst.

Operating Current-amps-I 1 7.7 8.2 8.4 6.812 9.2 9.2 10.0 8.013 8.6 8.5 8.6 8.0

I Power-watts ------------W1 240 220 230 220W2 190 170 200 200W3 140 120 140 110

Pedestal Speed -RPM--max. 6.2 6.2 6.2 6.2

Thermoeouple Readlings (deg F)

Positicn N.Outer Casting 7 78 150 -65 77

Thermoetat Well 8 78 150 -65 77Iznner Casting #1 9 78 150 -65 77Inner Casting #2 10 18 150 -65 77Rotary Joint-

Floating NT. 11 78 150 -65 77Oil Filter Top 12 78 150 -65 77Thermostat (Oil) 1 150 -65 77Heater 1 78 150 -65 77I 011-Dip Stick 15 78 150 -65 77Gear Mesh Oil Tube 16 78 150 -65 77

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.I HAZELTINE ELECTRONICS DIVISIONHAZELTINE CORPORATION

IREPORT 1007• Addendumi L

I ADDENDUM LSOVERTUTING MNOENT, ANJI•NNA ERECTION

When the reflector in assembled about its pivot point with its1i | top on the ground, Its oenter of gravity has a moment am of 72SIInches fcmo the pivot point. See figure I-1.

1Resitng Moment:n MR = M(R) (W) - (72") (1600*) - 1l5,200 inch-lbs.

I MR , 115,200 Inoh-lbs = 9600 ft-lbs.12

I Cable Tension:

(52.5)F1 = MR

F1 = 11.,200 Inch-lbs. 2200 lbs.52.5 inohes

When the reflector Is passing thru the "transfer point," theload Is gradually transferred from the lifting oble to the loweringcable of the bridle. The overturning moment goes from 9600 foot-lbs.,thiu zero* then gradually rises to a positive maxi•uum Just beforethe reflector Is erected.

Positive Moment:

Mp W (!p) (W) - (63") (1600*) - 100.800 Inch-lba.

Mp - 100A800 = 8400 toot-lbs.12

Cable TensioniF2 U 100,800 lnoh-lbs 1 5•00 lbs.

67 Inches

Iln Page L.P 22 AV 2 R


REPORT 10075 Addendum L

W+

I~~F -T°o.o.715." OFREFLECTOR

R E F L E C T O R .l - - - - 6 3 " it

I1800 LBS. I!7511114

GROUNDT0P OFREFLECTOR q II

i Figure Ll. Overturn moment Diagram

I ~Page U2

P 22AVZR


REPORT 10075 Addendum M

ADDENDUM M

TESTS ON GROUND ANCHORS

I. Screw Type Anchors

The earth anchor selected for the most common soil oondi-tions (Classes 5 & 6) is A.B. Chance Company's No. 10146, a 10 inchdiameter screw anchor with a 66 inch long shank. Its holding poweris rated at 10,000 pounds and 8,000 pounds for soil classes 9 and 6respectively.

The ease with which this anchor could be set in positionwas demonstrated for attending USASRDL personnel at Hazeltine Corp.Manufacturing facility, Greenlawn, N.Y. The anchor was rotated and

V driven into the ground (Class 5 soil) in approximately six minutes.Removal was accomplished with greater ease in approximately fourminutes.

To test its holding power in this soil, the anchor wasdriven into the ground and subjected to a pull test. Between theshank eye of the buried anchor and the cable of an M-35 truck winch,a dynamometer of 10,000 pound capacity was shackled. With thewinch operating, a 10,000 pound load was slowly applied to thescrew anchor. With the load maintained at 10,000 pounds, the anchorremained firmly embedded.

2. Arrow Head Anchor

The arrow head anchor is recommended for use in soilClasses 3 and 4, It is rated at 11,000 pounds holding power whenused in hardpan. In order to use these anchors, holes must be dugand the anchors inserted and buried. Either this, or the screwanchor previously described, may be used in Class 4 soil, whicheveris more expedient under field conditions. Generally speaking, thisanchor may be used wherever the field conditions are unfavorable forthe use of the screw type anchor. This type of anchor must be dugout to remove, whereas the screw type anchor can be backed out byturning its rod counter-clockwise.

3, Rook Anchor

The anchor, recommended for Class 1 soil conditionsiothe expanding type manufactured by A.B. Chance Co. The use of thisanchor requires the drilling of a hole 1 7/8" in diameter and onefoot deep In the rook. The anchor is slid down into the hole in therock, and the rod turned clockwise, causing the anchor to expand andwedge tightly against the inside of the hole.

ave Page M1P 22AV2RR


REPORT 10075 Addendum Y

I In this case it would be necessary to include a powerimpact tool (electric or pneumatic) and cutting tools to drill theanchor holes. Since the cutting tool is a perishable tool, a meansof re-sharpening or replacement at the site should be considered.Operation in rocky terrain will also be limited by the capabilitiesof the suppor'ting vehicles, and for these reasons is generally not

I con~sidered feasible.

4. Operation of the equipment in swamps and marshes (Class 8)wv-. not considered feasible owing to the inability of the supportingveh~oles to negotiate this type of terrain.

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P 22 AV 2 R

Titleof'Report: Final Report - Development of Antenna Group

OA-122?(XE-I)/TPS

Contract No. DA36-039 SC-74866 No. of Copies; 30

Contractor: Hazeltine Electronics Division ofHazeltine Corporation

DISTRIBUTION LIST COPIES

Commanding OfficerU.S. Army Signal Research and Development LaboratoryFort Monmouth, N.J. ATTN: SIGRA/SL-SR(T)

thence to SIGRA/SL-ADJ F&RU#3 1

SIGRA/SL-SRE 1

SIGRA/SL-DE 1

SIGRA/SL-ADT 1

SIGRA/SL-TN (3 aye) 3

OASD (R&E), Th 3E1065The PentagonATTN: Technical LibraryWashington 25, D. C. 1

Chief of Research and DevelopmentOCS, Department of the ArmyWashington 25, D. 0. 1

Chief Signal OfficerDepartment of the ArmyATTN: SIGRDWashington 25, D. C.

Commanding OfficerU.S. Army Signal Materiel Support AgencyATTN: SIGMS/ADJFort Monmouth, New Jersey 1

Commanding Officer9560 TSUU.S. Army Signal Electronics Research UnitP.O. Box 205Mountain View, California 1

Director, U.S. Naval Research LaboratoryATTN: Code 2027Washington 25, D. C. I

1

fA

DISTRIBUTION LIST (Cont'd) OOPIES

Commanding Officer and DirectorU.S. Navy Electronics LaboratorySan Diego 52, California

Corps of Engineers Liaison OfficerU.S. Army Signal Research & Development LaboratoryFort Monmouthq New Jersey

Marine Corps Liaison OfficerU.S. Army Signal Research & Development LaboratoryFort Monmouth, New Jersey

U.S. Continental Army Command Liaison Officer, Evans AreaU.S. Army Signal Research & Development LaboratoryFort Monmouth, New Jersey (3 0ys) 3

Commanding GeneralU.S. Army Electronics Proving GroundFort Huschuca, Arizona I

CommanderAeronautical Systems DivisionAir Force Systems Command, USAFATTN: WCOSI-3Wright-Patterson Air Force Base, Ohio (2 cys) 2

CommanderElectronic Systems DivisionAir Force Systems CommandATTN: RASSLDGriffise Air Force Base, N. Y.

.CommanderElectronic Systems DivisionAir Force Systems Command, USAFL. G. Hanscom FieldATTN: CROTRBedford, Mass.

CommanderArmed Services Technical Information AgencyATTN: TIPDRArlington Hall StationArlington 12, Virginia 3

(Classified reports furnished to ASTIA will bear thefollowing stamp on the cover: "Reproduction of thisdocument in whole or in part is prohibited exceptwith permission of the issuing office; however,ASTIA is authorized to reproduce the document forGovernmental purposes." )

2

DISTRIBUTION LIST (Conttd) COPIES

Chief, U.S. Army Security AgendyArlington Hall Station

- Arlington 12, Virginia (2 oys)

Deputy President, U.S. Army Security Agency BoardArlington Hall Station'Arlington 12, Virginia

This contract is supervised by Chief, Radar EquipmentBranch, Radar Division, Surveillance Department,U.S. Army Signal Research and Development Laboratory,

* Fort Monmouth, New Jersey (Telephone Eatontown, N. J.59-6-1313). Contracting Officerts Teohnical Representativesare: Messrs. Norman A. Abbott, W. Eittreim and V. L. Friedrich.

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unclassified ad 273106 - dtic · rotary joint, coax-to-waveguide transition and rf cabling are...

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