AEDC-TR-65-85

A SIMULATED ALTITUDE TEST OF A SATURN SIC RETRo DEVELOPMENT MOTOR

ITEST UNIT NO. So-20J

J. S. CLip l1li 8. M. Bishop ARO, Inc.

May 1965

ROCKET TEST FACILITY

ARNOLD ENGINEERING DEVELOPMENT CENTER

AIR FORCE SYSTEMS COMMAND

ARNOLD AIR FORCE STATION, TENNESSEE

HTTNIHEROICRELlCS.ORG

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A SIMUL ATED ALTITUDE T EST

OF A SATURN SIC RETRO DEVELOPMENT MOTOR

(TEST UNIT NO. SD-20)

... '.'" - , .. ,-

J. S. Culp and B. M. Bis hop

ARO, Inc .

FOREWORD

The work reported herein Wali spor'Ulored by the National Aeronautics and Space Adminis t ration (NASA) and The Boeing Company (TBC) for the Thiokol Chemical Corporation (TCC) under Program Area 92 1E, Project 9115.

The results o r the test presented were obtained by ARO, Inc. (a subsidiary or Sverdrup and Parcel, Inc. I, contract operator o r the Amold Engineering Development Center (AEOCI. Air Force Systems Command (AFSCI, Arnold Air Force Station, Tennessee, under Con­tract AI" 40(600)-1000. The teat waa conducted on February 24, 1965, under A nD Project No. HP1435, and the report was submitted by the authoz,s on April I, 1965.

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This technical report has been reviewed and is approved.

Ralph W. Everett Major, USA I" AI" Representative, RTF DCS/Test

Jean A. Jack Colonel. USAF DCS/Test

"' EOC,T I!,6 ~,U

ABSTRACT

Saturn SIC retro motor TE-M-424, Test Unit Number 50 -20, was fired in Propulsion Engine Test Cell (J-5) as par t of the use,"s, Thlokot Chemical Corporation, research and development program ror this motor, The primary test objectives were to determine ignition characteristics, ballis t ic performance, and hardware integri ty at alti­tude conditions . The motor was ignited, as planned, by t he t wo ignition systems at a simulated alt i tude of 113,000 ft and burned a t an average altitude of 113,000 ft for a total of 1. 5 sec. The effective burn time was 0.626 sec, and the motor produced a n effective vacuum impulse of 59,530 Ibf-sec, which is above the specification minimum of 57,3001br-sec . The ignition time of 92 msec is within t he specifica tion r equirement s. Post-lire motor inspection revealed that the hardwar e integrity was satisfactory.

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COHTENTS

ABSTRACT . · • • • • • I. INTRODUCTION. • •

ll. APP ARATUS 2 . 1 Test Article • 2 . 2 Test Cell and Installation . • • • 2 . 3 Instrumentation . • • • • 2 •• Calibration. · · · · · • •

ill. PROCEDURE • • • • · • • IV. RESULTS AND DISCUSSION

• . 1 General · · · · · · • • • • <.2 Motor Ignition. · · · · • • 4 . 3 Ballistic Performance . • • 4. 4 Motor The r mal Data . · • • • • 4. 5 Motor Structur al Integrity • • •

V. SUMMARY OF RESULTS . • • REFERENCES. · · · · · . •

ILLUSTRATIOHS

Figure

1. Saturn SI C Mockup a . Retro L ocation. • • • • • h. Retroa under Fairing . • • • •

2. Saturn SI C Retro Motor a. Over all View h. Sectioned View. c . Throat and Pyrogen Detail

3. Exploding Bridgewire Ignition System

4. P ropulsion Engine Test Cell (J -5 ) a . Spray Chamber and Elevated Tank . b. Ove r all T esting Complex ..... c, Artist's Cutaway View .....•

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d. Schematic or Thrus t Measuring System . e. Plan View . . . . . . . . . r . Interior View ...... .

5. Saturn SIC Retro in X-Ray Inspection

6. Motor Installation . . ...... . • •

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Figure

7. Motor Ignition Detail .. .. .. .. .

8 . Measured r.-totor Ballistic Performance.

9. Comparison of 50-19, 50-20, and Predicted Motor Vacuum Performance

a. Axial Force ... b. Chamber Pressure

10. Chamber Temperatures a. Thermocouple Location b. Data . . . .. .

11. Post-Fire Motor Condition

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Overall View . • . Close-Up of Nozzle Throat. Propellant Slivers

U8LES

Composition of TP-E-8104 Propellant

Countdown Sequencer Program . Summary of Motor Instrumentation

Summary of Molor Performance Data

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SECTIOtoi t

ItHROOUCTIOH

The Saturn V launch vehicle consists of three stages. SIC, s- n , and S-IVB, and the ins t rument unit. The first of the Saturn V stages, the SIC. has two TE-M-424 solid-propellant retro motors located in each of the four fairings, which are st the base of the stage (Fig. 11.

The nominal 800, OOO-ib thrust produced by these retro rockets pro­vides for s more rapid separation of the SIC and S-Il stages. thus reducing the time in which there is no vector control of the vehicle. Ignition of these motors is programmed to occur during main engine taHoH. After ignition, the motors are to burn through the fairing and decelera te the stage.

The TE-M-424 Saturn SIC retro motor is built by Th\okol Chemical Corporation (TCC). Elkton Division. Test unit number SD-20 (Serial Number 5007) was test fired in Propuls ion Engine Test Cell (J-5) at the Rocket Test Facility (RTF). This was the second and last firing of a TE-M-424 in an altitude facility as part of the research and development program for this motor . T he results of the (irst firing are discussed in Ref. 1.

Objectives of the altitude test were to de termine ignition character­istics when two Ignition systems are used, ballistic performance. and hardware integrity at altitude conditions .

2. 1 TEST ARTICLE

SECT lo.t II APPARATUS

Each retro motor has an approximate gross weight of ft20 lb and is designed to produce 100.000 lbf for 0.6 sec of its 1. ft - sec burn time. The overall weight is less than the 537 lb specified In Ref. 2. and the motor fits within the phys ical envelope specified.

The motor chambe r , 15.2 in. in diameter and 79 . 7 in. long. Is constructed of 1/8-in. -thick Ladish 1)(>6 s teel with a liquid polymer line r (TL-L-300) (Figs. 2a and b). A s ingle fixed 15-deg, half-angle nozzle having a nominal throat diameter of S . 70 In . is submerged 12.9 in. into the chamber. The submerged portion of the nozzle is con­structed of Ladish DC-S s teel. having a graphite throat insert backed

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by a cork and rubber composition gasket (Armstrong Type DK-149) and a cadmium plated steel retaining ring which is pinned to the nOl:de body (Fig. 2e). The outside diameter of the throat portion of the submerged nonle is insulated with a paper phenolic insulation material, whereas the remainder is insulated with T L-L-300. A tapered steel exit cone (AIS1 4130 heat treated per MIL-H-6878) extends the nOl:l:le from an area ratio of 3 . 7 to 8 . 7. A styrofoam nozde ciosure Is cemented into the n07.de at an area ratio of I. 6.

The chamber was loaded with approximately 278 lb of compos ite. case-bonded, polysulhde propellant (TP-E-8104) cast directly into the chamber in an internal burning twelve-point, double-web star g r ain con­figuration. Propellant composition is presented in Table I .

Propellant ignition is effected by a pyrogen- type igniter, which is ignited by two exploding bridgewire (EBW) initiators firing into a cavity containing Boron 2A pellets (Fig. 2c). T he system is armed by pro­viding 28 v to the EBW firing units that consist of a series of capacitors which accumulate a sufficient charge so that, upon applying the firing current to the system, a thyratron is triggered. supplying approximately 2300 v to the EBW initiators (Aerojet AGX-2008 Rev . K) (Fig. 3). This ignites 18 g of Boron 2A pellets which ignit e the pyrogen grain. The pyrogen exhaust passes through five 3/8-!n. -diam holes and Impinges on the motor grain at a 4~-deg angle. The 1. 75-1b pyrogen grain, cast in a double-web star grain configuration, is the same composition as the motor grain.

To determine the condition of the EBW firing units after arming and before firing, an EBW Firing Unit Monitor (Fig. 3) was constructed. This monitor verifies that the system Is armed prior to firing. indicates that the system has discharged. and relays the time of discharge to the end recording system.

2.2 TEST CELL AN D INSTA LLA TION

The Propuls ion Engine Tes t Cell (J- ~) (Fig. 4) is a horizontal test cell designed for testing solid-propellant rocket engines with a thrust up to 100,000 lbf (with a growth potential to 200, 000 lbf thrust ) at alti­tudes in excess of 100,000 ft. The cell is a cylindrical section 16 ft in diameter and 50 ft long and is fabricated from a 1/2-in. hot rolled steel plate reinforced at 6-ft intervalS with ring girders. It is insulated with 2 in . o f cellular glass , coated with 1/8-in. vapor seal mastic, and pro­tected by a O. 020-in . aluminum jacket.

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,o,EDC·TR·65·15

The single component th r ust stand used in t his test is capable of measuring axial forces in excess of 100, 000 lbr. Axia l thrust is reacted by two 33-1n. I-Beams, which are anchored in the cell founda· tion containing approximately 600,000 Ibm of reinforced concrete. The stand is stabilized in the yaw plane by a forward and aft column extend­ing through bellows seals in the wall of the test cell to a "seismic mass" consisting of approximately 600,000 Ibm of reinfor ced concrete. Cali­bration of the axial load cell is sccomplished, in place, by a binary deadweight calibrator having a range from 0 to 127,000 lbf. With the loaded Saturn motor and suppor t hardware installed, the thrust s t and had a natural frequency of approximately ~~ cps in the axial direction.

Two tandem steam ejecton (Fig. 4c) are placed in each o r four auxiliary ducts which are located circumferentially around the test cell at 90-deg intervals. The auxiliary pumping system is used for improve­ment of the test cell altitude or for removal of exhaust gases from thrust termination or other auxiliar y contr ol systems. Three of the ejector­duct systems were used during the Saturn tests.

The test cell is equipped with a temperature conditioning system designed to maintain the test cell and motor at the prescribed tempera­tur e from motor installation until just prior to pre - fire pumpdown .

The rocket exhaust discharged into a ~3- in. -diam, water-cooled diffuser having a two-s tep entrance cone (Fig. 4d) , which is inserted in a 102- in. -diam, water-cooled d iffuser. A center-body steam ejector installed in the 102-in. -diam diffuser is used to facilitate pre-fire pump­down, to maint a in altitude, and to reduce r ecir culation of gases into the test cell a t motor tailoff. The steam ejector has an 8. ~-in . -diam throat and an area ratio of 10. It may be cont rolled aut omatically or manually over a driving-pressure range from 0 to ~OO ps ig.

The exhaust-steam mixture then flows through a spray chamber 16 ft in diameter and ~O ft long which contains nine spray banks , e ach of which is capable of deliver ing approximately 9000 gpm at a maximum pressur e of 47 psia . Water is s upplied to the s pray chamber from an elevated water tank with a usable capacity of appr oximately 2~0, 000 gal. From the spray chamber, the exhaust gases flow through appr oximately 2000 ft of 13-ft-diam duct to the RTF exhaus ter m achines and are pumped to atmosphere as shown schematically in Fig . 4e.

To provide additional light for the high-speed (2000 fps ) opt ical data systems, the test ce ll was painted white, and a light hood waS fabricated (Fig . 40 . The hood consists of 48 reflectors, each having two long dura­tion (1. 7~ sec) flash bulbs . In order to provide the light required for three

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seconds , the r erJectors were div ided into three groups a rranged to pro ­vide equal light intensity ove r t he motor area . Ignition t imes are g iven as part of Table ll .

2.3 IHSTRUMEHTA TIOH

Axial thrust was nleasured using a nominal 100, OOO-lbf, fourfold­output, bonded strain-gage-type loa d cell . Unive r s a l n exures were us ed to iSOl a te the load cell from any fo r ce not directed through the load c ell axis . Strain-gage-type t ransducers were used to m easur e pyrogen, chambet· , steam, water, exhaust system, and auxiliary pumping syste m pressures. Motor case and nozzle temperatures were sensed with i ron ­constantan thermocouples bonded to the motor chamber and nozzle . Steam, water, exhaust system , and auxiliary pumping syst em temper a ­tures wer e measured wit h iron-constant an thermocouples.

The output signal of each measu r ing device was recorded on re­dundant end recorders . The types of data acquisition and recording sys ­tems used dur ing this test were a multiple-input digital data acquis it ion system scanning each parameter at a rate of 45 or 225 samples pe r second and recording on magnetic tape, single input analog continuous magnet ic tape, FM systems r ecor ding on magnet ic tape , photographically r e cording galvanometer-type oscillographs r ecor ding a t paper spe eds of 16 in. /sec 01' 80 in. /sec, and direc t -inking null-balance potentiometer­type st r ip cha r ts . Vis ual observation of the firing was provided by a closed-circuit television monitor . High-speed (2000 {psI opt ical data were obtained to pr ovide a pe r manent visual record of the firing . Table III presents instrument r anges , recording methods , and system accuracies fo r aU measured parameters .

2.4 CALIBRATION

The axial thrust inst r umentation systems were calibr ated a t alti­tude conditions before and after the motor firing by us ing a remotely controlled, hydraulically activa ted de adweight binary calibrator. T he axial th r us t calibr ator we ights are aecondary standard weigh ts certified by the National Bureau of Standar ds (NBS) to be in erro r by less than 0. 01 percent. By using a standar d load cell system, accu r ate to 0.05 per­cent, the ent ire axial thrust calibrator was in-place c alibrated from the 4000 to the 100, 000 lb( level.

All t ransducers used in this tes t we re laboratory calibrated befor e installation. The st r a ln-gage -type pressure transduce rs were in -place

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calibrated with an electrical calibrat ion system. A voltage substitution­type of in-place calibration was used on the thermocouples. They had a l~crF reference junction, and the NBS (Ref. 3) iron-constantan tables were used to reduce the data to engineering units. An in-place calibra­tions were performed at altitude before and after the firing.

SECTION III PROC EOURE

The motor arrived at AE DC January 29, 1965 , and was transported to the AE DC Radiographic Inspection Laboratory and subjected to an inspection with the Betatron X-ray machine (Fig. 5). On February 17, 1965, it was transported to the Rocket Preparation Area where the pres­sure transducers and chamber thermocouples wer e installed. A pres­sure check was performed following TCC Procedure OCL-T-2198 , Rev ision 2.

Prior to firing the firs t motor, an impulse test and linearity check were p~rformed on the thrust s tand with the mass simulated motor in­stalled to determine basic thrust stand characteristics. In addition, an EBW initiator was fired by each Ignition system, verifying the system's performance.

On February 19, 1965, the motor was transported to the test cell, installed in the thrust stand ( Fig. 6), aligned, and prepared for firing. This included connecting, checking, and insulating the instrumentation cables with asbestos cloth, aluminum foil, glass tape. and RTV-88 silicone rubber as well as positioning the diffuser entrance cone and checking the Ignition and camera systems.

The temperature conditioning system was started on February 19. and the test cell temperat ure was maintained between 62 and 75°F until 12 hr prior t o air-on. During the 12-hr period. the motor case temper­ature was maintained between 6S and S9"F . T his is wi th in the limit s of 70± ""F speclried by Tee.

On February 24, sea-level calibrations were performed followed by a sequence run, which verified that all transducers and end recording systems were operating properly and were acceptable for firing. Final test cell pre-fire operational procedures were completed; the test cell was sealed and evacuated by the RTF exhaust machinery to O. 34 psia (approximately 84, 000 ftl (Ref. 4). Altitude calibrations were then performed.

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AE ClC ·TR·6S-15

Approximate ly 65 sec prior to ignition, the automatic sequencer was started, activating the steam, water, light, camera, instrumenta­tion, and ignition systems at the times shown in Table II . Starting at T + 10 sec, the sequencer began the post -fire shutdown.

After post-fire al t itude calibrations were performed, the cell was returned to sea-level pr essure. The motor was removed from the test cell February 25. 1965. and ret ur ned to the Rocket P reparation Area for post-fire inspection. On March 2, 1965, the spent motor was re­turned to TCC by truck.

SECTION IV ItESUL TS AND DISCUSSION

U GENERAL

The results report ed herein are those obtained from the firing of the Saturn SIC Retro Motor SD-20 in P r opulsion Engine Test Cell (J -5) on February 24 , 1965 . In addition to ballistic performance, the objectives of th is test were to ver ify hardware In tegrity and igni tion cha r acteristics at al titude condit ions. The results, wi th the corresponding data f r om the test of motor SD -19, are summarized i n T able IV.

4.2 MOTOR IGNITION

Propellan t combustion was Initiated by one of the two exploding bridge ­wire ignition systems at an altitude of 113,000 ft(Re f. 4). The second EBW initia tor apparently fired 9 msec later. T he nozzle closur e, which sealed the chamber and igniter a t atmospheric pressur e, was ejected without damage to the nozzle or nozzle e xtension.

Ignition delay, defined as the time from receipt of ignition current by the EBW Firing Unit until chamber pressure reaches 100 psla, was 58 msec. The ignition rise time, which is the time required for chamber pressure t o change from 100 psia to 75 percent of its maximum value, was 34 msec. Ignition time, the sum of ignition delay and ignition r ise time , was 92 msec. This was less than the 130 msec required by Ref. 2. An analog trace of thrus t, chamber pr essure, and pyrogen pressure for the first 160 msec is presented In Fig. 7.

4.3 8"LLlSTIC PERFORWoNCE

A measured thrust-time curve is presented in Fig. 8 along with chamber pressure and cell pressure . Motor - diffuser pumping was

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,UDC·TR·U·I~

maintained throughout motor tailoff. The average altitude during the firing was 113,000 ft.

to.lotor operation t ime, defined as beginning at the first perceptible indication of thrus t and ending when the thrust falls t o zero, was approxi­mately 1. :'I sec. The effective burn time, defined as the ela psed time from the point where chamber pressure rises to 7:'1 percent of i ts maxi­mum value and ends when it returns to this value , was 0.626 sec.

T he average effective measured impulse based on motor effective burn time as determined by five high accura cy magnetic tape systems was 59,5101bf - sec. One s tandard deviation was O. 105 percent. Effective im­pulse, corrected to vacuum conditions by adding the product o f the cell pressure integral and pre-fire nozde exit area, was 59,530 Ibf-sec. This is greater than the requi red 57,300 Ibr-sec s tated in Ref. 2 . This correc­tion amounted to O. 033 perce nt of measured effective impulse. The aver­age effective vacuum thrust was 95, 100 lbf, which is within the required limits of 8 1, :'100 and 100,140 Ib specified in Ref. 2 for a 70"F motor.

Measured m otor operation, or total impul se, was 66,000 Ibt-sec. The vacuum corrected total impulse including the cor rection to vacuum con­ditions was 66,0:'10 Ibt-sec for a specific impulse of 234. 6 sec based on the user's s t ated pr opellant weight.

The maximum chamber pressure was 1700 psia . Average chamber pressure based on motor effective burn time was 1679 paia . Figure 9 provides a comparison between the results predicted in Ref . 5 , the results of the first test (50 -19), and those obtained in this test. T he predicted data s tarted at 100-psia chamber pressure . T his time was correlated with the ignition delay experienced on both firings and the composite plot m ade. The 50-20 effective burn time was longer (0.626 versus 0.610 sec) and at a lower chamber pressure (1700 versus 1760 psia max) than SD-19. Both motors had substantially the same throat area .

4 .4 ~OTOR THERMAL DATA

Fourteen iron-constant an thermocouples were installed on the motor as shown in Fig. lOa. Figure lOb present s a series of plots of chamber, nozzle, and cell temperatures versus time from T - 0 to T + 320 sec. It is noted that the disagreement between two corresponding thermocouples located at different web sections 30 deg apart is less than 25°F .

Alt hough cell temperature remained rela tively constant during the peak period, a ll of the chamber temperatures continued to rise , indicat­ing that they were insulated sufficiently to prevent t he cell tempe r ature from affecting the data significantly . The data indicate tha t the r e was no significant case temperature rise during the (iring even though post­fire temperatures reached 280°F at T + 320 sec when data ac quisition ended .

The nozzle exit cone thermocouples were bonded to the nozzle with epoxy cement in accordance with the user's r equest. Opt ical data sys ­tems indicated that thermocouples T-12 and T - 14 came completely un­bonded at T + I. 5 sec. Data analysis indicat ed that during post -fire heat soak these parameters approximated cell temperature .

Thermocouples T-II and T-13 e xhibited S and IsoF temperature rise, respect ively, during the I. 5-sec motor burn tim e. It is believed that these data are invalid because the optical data recorders indicat ed that the noz.:le pain t blistered during th is same tim e period . The post ­fire heat soak resulted in maximum indicated exit cone temperature s of 190° F (Fig. lOb) .

4.5 MOTOR $TROCTURAL IHTEGRITY

Post -fire inspection W ig. 11) revealed that all component s of t he motor were in satisfactory condition. The paint on the nozzle e xit cone started to burn at approximately 0.7 sec, and a portion of it was blown off at the end of motor operation (T + I. 5 sec). There was a consider­able amount of bluing on the exit cone with the hot spots corresponding to the valleys in the propellant grain configuration.

The nozzle thl'oat remained in place and showed no sign of m ajor erosion. Twelve propellant slivers, approximately 5/8 In. wide and 3/8 in. high, remained in the chamber. T CC estimated the r emaining propdlant at 3 to 4 lb. With the exception of the pr opell ant s liver s and the heating of the e xit cone, the condition of the vis ible par t of the motor was excellent.

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SECTION V SUMMA RY OF RESULTS

The results o f the firing of Saturn SIC Retro development motor SO-20 at a simulated altitude of 113,000 ft in Propulsion Engine Test Cell (J -5) are summarized as follows:

l. Structural integrity of the chamber, nozde , nozde extension, igniter, and throat was satisfactory.

2. With the pyrogen and chamber sealed at atmospheric pressure, the motor was successfully ignited by one ignition system as planned. The ignition time was 92 msec.

3 . The motor produced an effective vacuum impulse of 59,530 Ibf-sec which is greater than the 57,300 Ibf- sec specified in Ref. 2.

4 . Average effective vacuum thrust of 95, 100 Ibf is within the specification limits of 81, 500 to 100,140 Ibf for a 7Q o F mot o r.

5 . Twelve slivers 5/8 in. wide and 3/8 in. high remained in the chambe r after firing. TCC estimates that they contain 3 to 4 Ib of propellant.

REFEREHCES

1. Culp, J. S . "A Simulated Alt itude Test of a Saturn SIC Relro Devel­opment Motor (Test Unit No. 5 0 - 19) . " AEOC-TR-65-76, April 1965.

2. Retro Rocket MotOr Design P rocurement Drawing 60B47001 Originated by George C. Marshall Space Flight Center, NASA, Huntsville, Alabama, 5-17-63. Last Revision February 14, 1964 .

3. National Bureau of Standard s Circular 561, 1955.

4. Minzner, R . A. , Champion, K. S. W., and Pond, H. L. " The ARDC ·Model Atmosphere." AFCRC-TR-59-267, August 1959.

5. Black, R. E., Jr. "Internal Ballistics Report TE- 424 Rocket Motor." Thiokol Chemical Corporation RE-3S0, January 30 , 1964.

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S~ • , •

1 • ~ ' < , • u ~ ~

-

'" ~ ~ • , ,

• V " • ~ -• • -'l E

11 • • ~ u

IS-

AEDC·TR·'~·I~

26

• • - • " ~ • " • • • • • • • • >

• ! • " • , - • • , • ~ • .r • • • ." • • • • .. • •

~ • • ." • ~ • ... • I • •

- i • J - • • • • -•

27

• " -" --" " • " • • • • • • 1 - • • • , • • .t • i 0" j u

• • • • ~ ., 0 • • • • -• -• • •

•

28

..........

•

c ! I I • " f - , • • •

~

I •

~ q

-- j d • •

"

• • b. Dol.

F ill_ 10 Co""I..d.d

30

•. o...,.U View

Fig. l1 P .. ,·F, .. Mot ... CoIHIilloo

AfOC·lR·U·U

•

- i • • ~ 1 , •• • ~ ~ ~ ~ ~ • • • I , • • • , , u • , • · ' ~ ~ • -," . , -,

• • ." I •• , , • - u • • .-•

32

• 0 --• " & " 0

0 -• , -I • 0 -~ -• • • • 0 -• • • , ~ -, • •

's I

1 i --j ~ ~ = " •• • ,

33

AEO (:· TR·6 S·IS

TABLE I COMPOSITION OF TP·E·81(l.1 PROPELLANT

Percent by

Material Pur fl£se Weis:ht

Ammonium Perchlorate Oxidizer 72.0

Ethyl Formal. Sulfide . Type LP-33 Fuel and Binder 18. 8

Dibutyl Carbitol Formal Plasticizer 2 .•

SoH", l Diphenylquanidine Curing Agents 2 .• p-qulnonedioxiIne

Aluminum Powder Fuel 2. 0

Ferric Oxide Burning Rate Accelerator 2 . 0

Magnesium Oxide Stabilizer 0.0

T 65

T 50

T 40

T 38

T 10

T - ,

T - 2

T - \

T-O

T' \

T< 10

T . 15

T< 30

H 40

T + 320

TA8LE II COUNTDOWN SEQUEHCER PROGRAM

Start stea m system

Start wate r systems

Start d igital da ta acquisition system

Arm EBW ignition systems

", ED C·TR· 6$·15

Start st r ip charts, oscillographs B and C, a nd m agnetic tape recorders

Start oscillogr aphs A and 0

Start cameras

Fire firs t ser ies of photo flood bulbs

Motor ignition Fire second series of phot o Oood bulbs

Fire third series of photo flood bulbs

Stop oscillographs A and 0

In itiat e shutdown of water and s team systems

Stop strip cha rts and magnetic tape recorders

Stop cameras

Stop oscillographs B and C and digital dat a acquisition system

T ime in seconds

35

" TA8LE I II 0 >

5UIoIIoIAilY Of MOTOR IHSTRU.liEHTATlON " 0 Q

P aran,ele r SU-;p Oleillo' Hlah OIshal De.l. Syau,m, ~

Symbol Parameter Ranle C","" graph 1 ""cura"y FM SJ,mplu per ~cOfl(l • • Analol " -S,la'em • FY-I AlIlal Force o 10 I ~OK Ibt • A,. m 1"\,·2 Axial Force 010 ISOK Ibf C,D • ~'y- 3 A"lal Force 010 l S0K lbt' A, • • m 1'\'·4 Axlal FON:e 010 l S0K Ibf C, D • FY-li A_Ia\ Force 010 ISO K Ibf • PC·, Chamber o to 2000 pai, • A,. • m

PrUlure

PC-2 CMimber o 10 2000 pail C, D • P re •• ure

p p - , PyroCen o to 2:>00 plil • A,. m Pre •• ure

PP-2 Pyrogen o to 2500 p al. C,D • Preuure

PA-3 Cell Preuure o 10 O. f> pal a C,D '" PA - 4 Cell P reuure OtDO.Spall • A,. • PA oli Cell Prenure 010 15 pilla A,. m

T· ' Nozzle o to 1000"1" • • " Temperalure To> Ca ... o to 1000"1" • " T emperature T-3 Cue o 10 IOOO" ~' • " T emperature To< Forward Dome 010 1000"1" • " Temperatu r e

TAIlLE In (C ... d..H.I'

PaMlmeter Strip OIJCiUo- m,h DI,lIal Data 5yatem, Symbol Parameter Ranle Chari lraphl Accuracy '" Samplea per Second

Analo, 5latem

N Ca.e o to 1000"1" B .. Temperatllra

T-< Nonie o to 1000"1" C .. Temperatura

T-' Cua 0101000"1" C .. Temperature

T-' Ca .. o to 1000"1" C .. Temperatllra

T-' Ca.e 0101000"1" C .. Temperatura

T-IO F'orward Dome 010 1000"1" C .. Temperature

T-!! No~zle o to 1000"1" C ., Temperature

T-12 Nonie 010 1000- 1" C .,

T cmperaillre T-13 Nonie o to 1000"1" 0 ..

Temperature T -1 4 Nonie o to 1000"1" 0 .,

Temperature

E-I, 2 EBW Char,e ", A,B,C,D Monitor

I-I. 2 l, n llLon A,B,C, D .. Currenl

> "

V-I, 2 l,nllLon A,B,C,D .. 0 n

Volla,e • • • Io.clllo,raph.e A and 0 we .... operat ed at 80 in. Ieee durin, the tlrI",. o.cLllo,raph.e 8 • -~ and C were operated at 16 In./aee <!uri", the fiMn,_ •

~

AeD C_f R_65_U

38

TABLE IV

SUMMARY OF MOTOII PER FOIl MANCE DATA

( SATURN SIC RETRO MOTOR TEST )

Motor Number AEOC Tut Number Tnt Do.t~ Motor Environment durin!! the 12 lIouu

Prior to Cel! Pump nown. "I' Ipitlon Altitude. ft Avera,e Altltude. It Propellant M ..... Ibm " Pre-Fire Throa' A,..,a. tn. 2• Poot-Flre Throat Aru, In. 2

Pre-Fire Exit A,.., •• In.2 Poot-FI,.., E.U A,.., •. In. 2

Mo.or Welllhi. lb . M .... Rallo' [,nlllon Pelay. maec ill"Ulon Time. moee Eftectlve Burn Time. moee Total Burn Time, -ec Maximum Chamber Pre .. u,..,. pola To.al Cluomber Prnour. Inle,ul. p.l a -oec Effecllve Cllamber Prenure lo.ee.al. p.la - oec Avera,e Effective Chamber Pre .. u,..,. pol. Total Impul ••. Ibr-'''''

Meaoured V~cuum

P.,...,en. Vacuum Cor,..,etlon Effectlv., Impuloe. lb/-o.,c

Meaoured Vacuum P.,...,,,nl Vacuum Corn:ctlon

Avera,e Effect;ve TIt .... I. Ibf Muoured Vacuum

Specific Impuloe, aec TIt .... 1 CoeffiCient, vacuum

.Motor manu!ac.u,..,r·. data

SO-IS N P143~-01

2/18/65

68 10 71 114.000 113.000 280. 2S 35. 10 35. 10 306. 3~ 301.16 521. 25 O. ~4 .. " ." U 1165 Ill! 1041 1716

66.0901

66. 140 0.076

59,2102

MI. 230 0.034

9 7.080 97.100 236.0 1. 61

ll'lve data recordinll ay.tem rUdln," 'O'ere ave raged . " "bt.in 1M. value.

2Th,..,., dala ,..,cordl,.. .y.tem ,..,adlnll_ we,.., ave .... i1ed 10 obtain .hl_ value. Oliltal .y •• .,ma not uoed b~~.u.., of ""_I>O.,.e ehRr-acteritll!c._

50-20 RPI43~-02

2/2 4/ 6~

66 10 69 113.000 113 . 000 281 . 5 35,08 35.08 306. 26 306 . 8~ 527.00 0.53

" " ." U 1700 lUI 1051 1679

66,000 1

66,050 0.076

59.5101

~9. 530 0.033

95.060 95. 100 234 . 6 1.62

;:.== UNCLASS IFI ED

Center ARO, Inc.,

Tennessee

II SI MULATED ALTITUDE TEST OF II SATURN SIC RETRO DEVELOPMENT MOTOR (Test Unit No. 50-20)

N/A

" Culp, J. S. and Bishop, 8. M., ARC, Inc.

C_'~.CT" •••• ~T ~~ .

AF40(600 )-lOOO ~ Program Area 921£

• N/A

,

may obtain copies of this report from DOC. and foreign announcement and distribution

and Space

Sa turn SI C retro motor TE-M- 424 , Test Unit Number 5D-20, was f i r e d as part of the Thiokol Chemical Corporation research and development program for this motor. Primary test object i ves were to determine ignition character istics, ballistic performance, and hardware integ­rity at altitude condi tions . The motor was ignited by the two igni­tion systems at a simul ated altitude of 113,000 ft and burned at an average altitude of 113,000 It f or a total of 1.5 sec. The effective burn time was 0.626 sec, and tbe mot or produced an effective vacuum impulse of 59,530 Ibf-sec, whicb is above the specification mi n imum. The ignition time of 92 msec i s within the spec ification requir e­I;,:::", Post-fire motor inspection revealed that the hardware integ­

I : was s atisfactory.

UNCLASS IFIED Security CI ... lfluli""

UNCLASS I F I ED s.,elUi' Clu.ifico, i""

" ~ I"" • ~' N" • ..," " C U V .O~ b' 0 ... . ., ~ ... , " 0." "

Sa turn SlC Rocket Eng i ne

Alti t ude Tes ting

Re trograde Engine

INSTRIlCTIONS ,. O R,,,,"A">iG ACTIVITY, "'", .. , .. " ........ _ ... ;_.0<1 b •• ",",h, . , ... tr,."",". ""ne .. ...... 011 ... , .... " .. of ,~. <0 .. ,0<'0< ••• "0<""'0<' '''. " ....... 0 ...... -.,. of o. • ""h ... fo" ... .."i.", Of o,~ .. 0".,,1 .. 110" «_ ... ... 'hot) 1,,"1 ..

'" ··Qu.lIfiod ,*q" ... , .. . _. "'"in ..... , •• of 'hi. , ... "po". ,_" fto .. ODC.··

" REPORT IEC1.J .. Tv CI..AS$' I'ICAnO N, t .... , ,,,. ..... '" •• 1' .... , ....... ""e ........ od di .. _I""I." 0 ' , ..... ." '.'''HIt. <I ••• m" .. ;' •• f ,h. ' ...... I .dl< ... "" .. b .. ,_"., ODC I. ""' .",100., ..... " ··R . .. "", ... D.,,·· ,. ,"", .... eo<. M''' 'ne L. ,. b. L" .. _.s.

."« ... .,h .""tOP"'" '"'''''' , . .... "on .. '" "U S. Go ................ ""1 ..... , .... 1" e .... l .. 01

" C ROUP : A"'om.he do .. "C'odinc I, _elll,d I" DoD 01· ,hI • .--" dl<",U. ho .. ODC. Oth ...... 1111 ... DDC

,«"to .. HOG. 10 ond A' ..... 1' .. " .. I.,"".",,, 101 .... ". , .. " ..... """1 .. "" , " ,ho.""h

, ... . ' ...... _" . ..... 0 ... 110. 'OPU",bl . ..... w ",., cp'I.",,1 .. ",,,. ,, •• h.v. hoe" """, '" Go .. P J . ... Go_' ••• "' .....

'" ·'U. So ... Ih., ...... d ....... ",.;" «>P'" 01 ,hi. ".d ,.." 41NdL. I ..... DDC. O,h ...... Il/I .. "MI, ,. R D'ORT TITLE: 1>00., , ... <e..,h • • ' ...... "". 'ft "" .holl ' ...... , ' ....... h ",p'''' ,.n ..... Tltl •• I. ,n co.u ._,~ b. "".1 . .. 111 .... .. If. """'ncI"' "". "'''''''' "" •• 1"" ... .." ...... <1 ... 111 . ...

'" "00. ...... "U. <I .... """;." ,".n " •• "." , •• _",h •• 11 •• ... U ~I .. 'I""U •• of ,M. ,_" I. <0"' ... " .... "' .. , .. ,.<";0101. foU.,,, .. ,,,. "" •. llI.d DDC " . ....... LL ...... at ""_h

'. DESCR IPTIVE NOTt!< If ~"""""" •• ", .. ,he '''''" 01 " '<1''''' ...... , ... " .... P.-- . .... " ....... . ,"". •• , ... 11 .. 1. If ,he _" h .. ""on f ......... d to ' ... om • • • 1 T.d .... "" G,,·. , .... ' ... 1 ..... dol .. .. ""' ....... ,;. '-"",inc p." .. 4 L. 5 . .. 1< ••• O ........ "' .. f eo"""" ... ' M ""'. ,h. p>bU<. I.d~ ,,~,.~ .... e, .. ,hi. f"" . ... . "' .. ,h. p.'''. if ~ ...... , AlIT l«")~1'~ En< .. " .. ".ono1o.l el ... , ... «.) ......... o.

" SU PPLEMEIfTARV NOTES: U_ lor .dd"i""" • • pl . .... ., '" , ..... "" .. ,. 0:.., .. 'oa' ...... Ii .. , " ..... oU6dI. I .. ,U.L '''1 ... , . .. 11 ".",," •• _hO .... "" .oJ ",.""h e' . .... co. T"" "._ of ,b •• ""< ••• , .· .ho, ..... b.ol., ... ,"""" .. ".,w' ...... L " !WQ"OORI H() MILITARY ACTIVITY, E, ... , ........ 0.

• Rt:POfIT D"T~ Eft' .. ti,. dol. 01 ,'" , .... " .. d.y. 'h, 4~",_",.1 ptolK' .!fIoo ., '_"'0'' ....... ri". [ .....

_"' ... p'" or _ ..... y'''. ,,_. ,ho" 0 ... dot. ""p"" ' ... , •• ), he ..... "'h ........ '.p .... L '""'.4.0<1<10 ....

0" ,h. ' .......... dOl. 01 p • • "<'''.'' " ... BSTR ... CT , En",," '."",e' , i."" . ... of ."4 I.<t".,

" TOT ... L NIl " !) ER 0 .. P ... GES: T"" ,ot.l P'CO ew .. ." ........ , .... d"" .... ,,' 'nd'''''''' .f ,h. ~I"'''. ov_ '_.h " ..... , ....... " ."."h.,. '" ,h. bod. of .. " ""hni .. J .. _

.hooJd foU ... 00" ." ..... 1., .. , •• "'''''''''''''. I. ........ ,he po". If ,"H,.n.' .",eo " ... ~.I .. ~ .•• """""." ... h . ... ho ll ...... , .. 0' P'U' <o" ,ln,". ,.,., ... " ... .. ."."".d.

" ~ U ""ER OF REFt" tNC ES< En, .. ,,.. 'ot ol n.""" of It I, hi",', d •• ,,.b'. ,k., ,~ •• b""", of d ... lllod ........ .. I ... "" •• ~i, '" In ,h. ' ....... "" ...... 1 .... II.d Each ....... "" 01 "'. 0",,,,,,, .... 11 o"d .....

•• CONTRACT O R GR ... ST NU"UER, " -cp""', ."' .. •• ' .... 1< " 1"" 0' ,h~ .. "" • ., .. e.ri,>, el."III .. oo" o' , ... "' . ,1\0 _h •• tl . ......... . f ,'" .<In''''' .. ... .. • "" .. "';,:h f"""." ... ,. ,h. ",,, , .. ,,,, ........ "'.d .. f"S) . m . Ie,.", IV, ,h. ,.,,,, ......... ,,, ...

Th .... I' " G ".",,1 ... "" "'. ' ... ", of ,ho ... ".<1. Ho .. · ". a. ....... PR"OJECT )lU .. By ..... f.,o, •• , .. _,cpd ... ' '''. ,ho ,,, ••• ,,.d '''Cl~ " ltoe L$O '0 n~ ....... .. ;h, ............. '" ' ..... "lIc .' I ..... e h ••• ""oc' .......... ... K<::Y WORDS, K .. .......... ,.eh",<on ...... "'. M """. 0."" ... , .. , .... ""' ..... " ........ b ....... ~ n"""',, • • 'e ... h." ph ..... , ,,. , <hotK"" ..... po ... "d • .,. .. "Old .. •• OMIC1I1ATOR ·S REPORT 1IU""Ii:II(S), Ent .. ,ho . m· ; ..... ........ fot <" ., • • ''', .... ~po". Ke-," "0011. ".11 too ~ .. , ,_" " ...... b. ,,1tI<h ,he d"" ....... ' ... ,,, .. , ..... ~ , .... . ., ... ,.d •• "'" "0 '«""" ", ... ,/ie." ..... _., .. d. 140" ~· .n4 co .. "U.d b. ,h •• <I,ln,,''''' 0<,1.",. Thi. "".r.b .... , .. , Ii . .... ..,," ... q.i ....... ' """'., "'''CO'''''''. , .. do .. _ . ",II" ... b. unique , .. ,h ... .,....,. ....j." .ed. "' ..... ,o."phl" '''''.'' ... . ... , ..... d .. ~ •• .. OT "ER IUYOorr )l UllbtR(S): If ,h. ,,,,0" h •• b . ... .... d. bt" ,,'11 .. 1.,,_.4 ... '" ;"d,,,,,, ,,,, .1 ,«h.'co 1 < ... .

""I""d .", .,h .... _" ".""' ... ( .. ,h., h ! ...... ; •• ~."" ... ,. Th .... 1 ...... "' .. 1 " .... . 'u''' ......... ,"' .... opd ..... ' .

.,~" 'h .,.'"" .. A .1", ""to, ' ..... ""_.). '" ... VAU ...... U" .. 1T Y 1t.l lflT ... T IO N NOTICE!> Enle' ,ft. I;,.. ".Ii ..... on , .. ,he, d" .. m",.".".' , ... """" . o,h. , ,h." , .....

UNCLASS I F I ED