alouette s-27 press kit

8/8/2019 Alouette S-27 Press Kit

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N EWS R ELEASENATIONAL AERONAUTICS AND SPACE ADMINISTRATION400 MARYLAND AVENUE, SW, WASHINGTON 25, D C.TELEPHONES WORTH 2-4155---WORTH 3- 1110FOR RELEASE: Saturday a. m,September 22, 1962Joint U. S.-Canadian-release i7c. 62-189

PRESS KITon

THE ALOUETTE (S-27)U. S.-Canadian Space Project

Table of ContentsI General News Suwmiary *..e......o.... Page 1

( II Alouette Project Participants ......... ... Page 4III Thor-Agena B Vehicle and Launch Comples ... Page 7IV Auroral Ionospheric Conditions and theExperiments . ..... ....... Page 12

V NASA's Topside Sounder Program ............ Page 17,,I The Alouette Spacecraft and Related In-formation (Ground Complex; DataProcessing and Analysis; Supportingand Auxiliary Fxperbients) ....... Page 19

VII The Canadian Defense Research Board ....... Page 28

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ALOUETTE (8-27) PRESS KIT

Point Arguello, California -- in a joint undertakingby the United States and Canada, an attempt will be madeto place into orbit the Canadian Alouette satellite, thefirst international spacecraft to be designed and builtby a nation other than the U. .. or the Soviet Union. Thelaunching will be no earlier than September 26.The launch of the ionospheric topside sounder space-craft into a planned near-circular orbit of about 600 milesaltitude around the earth will be attempted with a two-stage Thor-Agene-B vehicle. This will represent the Nation-al Aeronautics and Space Administration's first orbitalattempt from a West Coast launch site as well as its firstuse of the Thor-Agena B vehicle. The name "Alouette" comesfrom a high-flying song-bird of the lark family which in-habits most of Canada.

The firing into the Pacific Missile Range of the space-craft built by civilian scientists of the Canadian DefenseResearch Board marks one part of a broad program by NASA tomeasure ionospheric electron density distribution and tostudy its variations.The Canadian satellite project is part of the Top. .deSounder Program under the management and technical direc-tion of NASA's Goddard Space Flight Center at Greenbelt,Maryland. The Alouette and the U. S.-sponsored s-48 to belaunched later this year, will support each other in iono-spheric investigations. ProjectYanager for the overallNASA program is John E. Jackson, a senior ionosphere physi-cist at Goddard.

Thc spheroid-shaped Alouette will conduct four experi-ments, three for the Defense Research TelecommunicationsEstablishment (DRTE), near Ottawa, and a fourth on behalfof Canada's National Research Council (ARC).


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A fabrication technique, originated in Canada, willgive the spacecraft a unique feature -- a .150-foct radioantenna -- believed to be the longest to date in a spacevehicle. Associated with it will be another antenna --7 feet, from t ip-to-tip. Both are made of thin, heat-treatedsteel and are stored on dirums wvitrhin the spacecraft- much likea carpenter's tape rule. They will be extended after the-;c ueiite has separated from the launch vehicle. Testingof' t~hese antvennas cesign and the feasibility of topsidesounders ,as carried out at NASA's Wallops Island StationIn Virginia by rocket firings in June 1961.

The 320--pound Alouette will be launched in a south-easterly direction into a near-circular orbit of 80 degreesinclination at an altitude of about 600 mates. It will orbitthe earth about every 105 minutes, pascing 10 degrees oflatitude from the north and south pole,.

Approximately 6,500 solar cells, covering the outerspacecraft shell, will provide power for the researchinstrumentation by converting sunlight into electricalenergy Go charge the satellitets batteries. The RFtransmissions will be terminated automatically after ayear.

The primary Alouette experiment will employ topsidesounder instrumentation to probe the ionosphere below theorbiting spacecraft to the F2 maximum (300-400 mn). Thesounder will attempt for a year to measure the way thenumber of free electrons in the ionosphere changes dairywith the time of day and latitude. This will be accomplishedby sending out "sweeping" radio signals from 1.6 to 11.5megacycles.

Two other DRB experiments will measure the galacticor radio noise that appears to originate in outer space,and the radio noise produced within the ionosphere itself.NRC instrumentation in the satellite will conduct thefourth ex:periment by observing cosmic rays, the energeticparticles which enter the earth's atmosphere from the sun

and from cosmic space.Design and constructi.on of the spacecraft was carriedout by DRTE with assistance from Canadian inducifry and NASA's

Goddard Space Flight Center. Much of the final testing ofthe spacecraft took place at Goddard, and the Center willcontribute to the data collection phases by tracking thesatellite and obtaining telemetry records at its world-wideMinitrack station network. NASA also is providing the Thor-Agena B launch vehicle.

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Scientific data will be obtained at 13 ground stations.The world-wide locations of the telemetry stations whichwill cooperate in collecting data further emphasizes theinternational flavor of the project. Three stations haveJeen constructed in Canada by DIT and will be manned byCanadian personnel. Two stations -- one at Singapore andthe other in the South Atlantic -- will be operated byGreat Britain. Eight of NASA's Minitrack stations also willtrack and record data.

While the long antennas are sounding the top levelsof the ionosphere from above, the lower layers will besounded at various locations by ground-based equipment.Comparisons of the topside and bottomside results will helpto establish the relationships sought by scientists.Data collected by the telemetry stations will be forwardedto DRTE for reduction and analys.s at a recently-establishedanalysis center. The scientific information obtained will

apply directly to radio communications and will be forwardedto world data centers, where it will be freely available toscientists of all nations.Acceptance of a proposal for the joint NASA/DRB

exoeriment was announced in the spring of 1959 followingdiscussions by Dr. T. Keith Glennan, then Administrator ofNASA, and Dr. A. Hartley Zimmerman, Chairman of Canada'sDefense Research Board.

While DRB has contribute in the past to several U.S.space research projects, the topside sounder experimentmarks Canada's first space satellite effort.

Some ultraviolet radiation from the sun directed toward earthis "stopped" or absorbed in the atmosphere at heightsranging approximately from 50 to 250 miles. Part of thisenergy heats the atmosphere and some of it splits neutralair particles into electrically charged ions and electrons,creating, in effect, an electrical conductor high in theatmosphere. This region, which surrounds the earth andhas the properties of a spherical reflecting mirror fo rradio waves because of its shape and composition, is calledthe icnosphere.

Reflection of a particular radio wave length isaccomplished only if the electrons are dense enough toact as the wall that will bounce them back. However, groundsoundings utilizing this method cannot reach altitudes abovethe maximum electron concentration (known as the ?2 regionwhich exists at 300-P00 km), hence, tche need for the satellitesto probe from above,

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PROJECT PARTICIPANTS

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION (NASA)NASA Headquarters, Washington, D.C.Dr. Homer E. Newell, Director, Office of Space SciencesDr. John E. Clark, Associate Director and Chief Scientist,Office of Space SciencesDr. John E. Naugle, Director, Geophysics and AstronomyProgramsMr. Arnold W. Frutkin, Director, Office of InternationalProgramsMr. M. J. Aucremanne, Project OfficerGoddard Space Flight Center, Greenbelt, Md.Mr. John E. Jackson, Project Manager and Chairman ofAlouette and S-48 Working GroupMr. E. D. Nelsen, Assistant Project ManagerMr. G. W. Ousley, Thor Agena-B LiaisonMr. J. F. South, Operations ControlMr. G. H. Melton, South Atlantic StationMr. Royal Tysdal, Systems Test and Evaluation

CANADIAN DEFENSE RESEARCH BOARDDefense Research Telecommunications EstablishmentMr. F. T. Davies, Chief Superintendent, DRTEDr. J. H. Chapman, Deputy Chief Superintendent andProject ManagementMr. J. S. Johnson, Superintendent/Electron cs LaboratoryDr. R. C. Langille, Formerly Superintendent/ilectronicsLaboratory

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Mr. R. K. Brown, spacecraft Project Supervisor andS-27 Mission DirectorDr. J. N. Barry, System DesignDr. C. A. Franklin, Systems DesignMr. W. E. Threinen, Power SuppliesMr. John Mar, Thermal and Mechanical DesignMr. H. R. Raine, Launch Site EngineeringDr. J. H. Meek, Superintendent/Communications LaboratoryDr. A. R. Molozzi, Satellite ControllerMr. J. N. Bloom, Ground Telemetry Stations and Data CentreEquipment - Design and ConstructionMr. E. E. Stevens, Ground Stations OperationCanadian Armament Research and Development EstablishmentMr. F. D. Ward, Thermal and Vacuum Testing Facilities

NATIONAL RESEARCH COUNCIL OF CANADADr. D. C. Rose Cosmic Particle Experiment Design

and ConstructionDr. I. McDiarmid

Data UsersDr. E. S. Warren, DRTE, Ionospheric Sounding DataDr. T. R. Hartz, DRTE, Cosmic Noise DataDr. J. S. Belrose, DRTE, Low Frequency Noise DataDr. C. A. Franklin, DRTE, Satellite PerformanceDr. D. C. Rose, NRC ) Cosmic Particle DataDr. I. McDiarmid, NIRC

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United Kingdom - Data UsersRadio Research Station, Slough, Burks, England

CANADIAN CONTRACTORSDeHavilland Aircraft Co., TorontoMechanical Design - Design anal fabrication of spacecraftstructure ;le) the mechanical design,development and construction of thelong sounding antenna system.Sinclair Radio Laboratory, TorontoAntenna Design - Electrical design of the sounding antennasystem ,nd match-ing network and also ofthe telemetry antenna system.R.C.A. Victor Co., Ltd., MorntrealTelemetry Transmitter - Design and production of thefrequency modulated telemetrytransmitters.

UNITED STATES CONTRACTORSLockheed Missilesand Space Company

Agena-B second stageBell Aerospace Co.Douglas Aircraft Co. TNorth American Aviation, Inc. TBell Telephone Laboratories - Guidance system

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THOR AGENA-B VEHICLE AND LAUNCH COMPLEX

The National Aeronautics and Space Administrationwill use a Thor Agena-B vehicle when it attempts to launchthe Canadian S-27 topside sounder satellite, Alouette.The launch into the Pacific Missile Range will be NASA'sfirst orbital try from a West Coast launch site.The Marshall Space Flight Center has the responsibilityfor providing the launch vehicle with the support of the

Air Force Systems Conmmand's Space Systems Division.Major contractors involved in the vehicle operationare Lockheed Missiles and Space-Co. and Douglas AircraftCompany. The vehicle will be launched under the directionof the Marshall Cen~erts Light and Medium Vehicle Office.The Marshall Center's launch vehicle systems managementresponsibilities include: Control of changes in the vehicle

system to meet NASA mission requirements, resolving ofproblems encountered in the integration of the launch vehicleand spacecraft, and direction of the launch operations.

LAUNCH FACILITIESThe space vehicle will be launched from a recently modified

launch complex. The rubber-tired, portable service towerstands 151 feet high. Utilizing existing equipment madeavailable to NASA, officials estimated a savings of tenmonths construction time and a million dollars on the facility.Cost of moving the service structure was $325,000; new equip-ment and construction cost $175,0CO. Cost of replacement tothe government would have been about $1.5 million.

Construction, operation ani maintenance of the modifiedlaunch facility is the product of joint efforts by NASA, AirForce, Navy and Army.

The Air Force, in addition to providing the basic Thor padstructure, is providing NASA with administrative management forcertain of the pad modifications through the space systemsdivision's 6595th Aerospace Test Wing at Vandenberg. The6595th also maintains and operates the launch complek. Crewsfrom Douglas Aircraft Co. and Lockheed Missiles and SpaceDivision will support the launch.

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The Army provided a surplus Redstone service tower andacts, through its Corp of Engineers, as agent for the AirForce in monitoring the execution of DTASA's constructioncontracts.The Navy suppoi'ts INA>K- Agena ptogrrams in thc operationof the Pacific Mssile Range to obtain radar and telemetrydata for satellite launches and has the responsibility forrange safety. PMR also provides NASA with facilities andsupport services at the Naval Missile Facility, Point

Arguello, California, and at PMR Headquarters, Point Mugu,California.LAUNCH VEHICLE FiLIGHT PLAN

The vehicle will be launched at 172 degrees from PMR.Its orbital. inclination will be 80 degrees prograde, eightdegrees east of polar orbit.The Thor main engine and vernier are burning at liftoff.The Thor is programmed to burn about 22 minutes. This phaseconsists of a vertical ascent followed by a programmed roll,

then a pitch down and yaw steering program into the desiredtrajectory, on which the vehicle continues until the requiredvelocity has been attained.The Bell Telephone Laboratory ground guidance computerdetermines the required velocity at which Thor vernier cutoffoccurs and coast begins. Acting on this data, the computerestablishes a signal through the Thor airborne guidance systemwhich initiates a timer adjustment aboard the Agena to compen-sate for booster performance dispersions. This timer in theAgena stage controls the sequence of events which occur afterseparation from the Thor. When vernier cutoff occurs, the

entire vehicle goes into a coast phase of about half a minute.Small explosive charges release the Agena stage carrying thespacecraft from the Thor.Retrorockets on the booster fire, slowing its upwardflight and allowing the Agena to separate. Then the Agenapneumatic control system begins a pitch maneuver to orientthe vehicle into an attitude horizontal to the earth. Thispitch maneuver is programmed to be completed before the timersignals ignition of the Agena engine.At engine start the hydraulic control system takes over,

keeping the vehicle horizontal during the approximately 2-1/2minutes the engine is operating. During Agena first burn, ata point where aerodynamic heatiig is no longer a problem, the-8-


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shroud protecting the spacecraft will be ejected. The infra-red horizon sensing device sends minute corrections to maintainthe correct pitch and roll attitude of the vehicle.If all events have gone as programmed, at Agena cutoffthe vehicle and its spacecraft will be in a transfer ellipseto the final orbit attitude.The Agena then coasts in this transfer ellipse for about48 minutes. The pneumatic control system again takes over,maintaining the vehicle in the proper attitude with respectto the earth. At the proper instant, the timer again signalsthe Agena to begin operation. The second burn is programmedfo r about four seconds. About one and three-fourth minutesafter the final engine shutdown, the spacecraft is given aspin velocity for stabilization and is separated from theAgena by springs. This occurs about one hour after liftoff.At separation from the Agena, the S-27 spacecraft shouldbe in a circular orbit about 600 miles high.

AGENA-B SECOND STAGEThe Agena-B stage of the rocket is an improved and enlargedversion of the Agena-A, which is used in D.O.D. programs.The Agena-B has integral, load-carrying propellant tankswith twice the capacity of Ageria-A uanks and is powered by aBell Aerospace turbopump-fed engine. It burns unsymmetricaldimethylhydrazine (UDMH) as fuel and inhibited red fumingnitric acid (IRFNA) as the oxidizer.The new engine develops substantially higher performancethan prior Agena engines and has a multiple start capability.Ullage rockets are used in preparation of the propellant systemfor restart. Firing of the ullage rockets gives the vehiclethe necessary acceleration to collect fuel and oxidizer at thebottom of their containers prior to reignition.The rocket's guidance system is capable of establishingattitude references and aligning the vehicle with them duringthe coast and engine operation phases. It also initiatesprogrammed signals for the starting, stopping and maintainingof various equipment during flight.Here is a sketch of the Agena-B:PROPULSION: Single rocket engine using liquid propellants,inhibited red fuming nitric acid and unsymmetrical dimethyl-hydrazine.

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THRUST: 15,000 pounds at altitude.SIZE: About 22 feet long.PAYLOAD: S-27 Canadian satellite, Alouette.CONTROL SYSTEMS: Pneumatic, using high-pressure gas

metered through external jets for using during coast phases.Hydraulic through gimballing rocket engine for pitch and yawcontrol during powered portions of flight. Both fed byprogrammer initiated by airborne timers. Correctionsprovided by airborne guidance system.

GUIDANCE: The guidance system--which is made up oftiming devices,, an inertial reference platform, a velocitymeter and an .infrared horizon sensing device--is entirelyself-contained.

CONTP&!(TORS: Lockheed Missiles and Space Company, prime-contractor:_2ETl Aerospace Co., engine.

THOR DM-21 BOOSTERThe Thor booster has already achieved a high-reliabillity

record in launches for the Air Force and NASA. It was thebooster which recently served in the launching of the Telstarcommunication satellite.

Here is a sketch of Thor:PROPULSION: Main engine and verniers 'burning liquid

oxygen and kerosene.THRUST: 170,000 pounds.WEIGHT: 107,500 pounds (fueled).GUIDANCE: Bell Telephone Laboratories radio command

guidance system mounted in second stage and roll and pitchprogrammers in first stage.

CONTRACTORS: Douglas Aircraft Co., crime; RocketdyneDivision of North American Aviation, Inc., engine.

KEY MANAGEMENT PERSONNELAgena-B direction at NASA Hcadquarters is provided by the

Office of Space Sciences, headed by Dr. Homer E. Newell. TheAgena program manager is Dick Forsythe.

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The field installation charged with managing the vesicleprogram is the NASA Marshall Space Flight Center headed byDr. Wernher von Braun. Hans Hueter heads the Center t s Lightand Medium Vehicles Office. Fredrich Duerr is the Agenasystems manager.Major John G. Albert is the director of the NASA Agena-B

program for the AF Space Systems Division, assisted by MajorCharles A. Wurster.

Harold T. Iuskin is the Lockheed Missiles and SpaceCompany manager of NASA programs,Launches from PMR will be conducted by the Light and Medium

Vehicles Office of Marshall. Major Jazaes P. Murphy heads theMarshall Office at PMR.

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IV

AURORAL IONOSPHERIC CONDITIONS AND THE EXPERIMENTS

The Canadian scier.tists responsible for the Alouette pro-Ject are concerned primarily with the upper regions of the ion-osphere above Canadats high latitudes. Some of the radiationdirected from the sun. towrards the earth. is absorbed in the ion-osphere which exists approximately 50 to 250 miles above theearth. During this absorption process, heat is produced andneutral air particles split into electrically charged ions andelectrons. They create in effect, an electrical conductor withthe ability to reflect waves from radio transmitters to re-ceivers.

When the ionosphere becomes excited following solar stormsor other phenomena associated with the sun, its reflecting prop-erties lessen or disappear temporarily. Consequently, radiocommunications are disrupted, sometimes for lengthy periods.Hence, the deep interest of Canadian scientists in studying theupper atmosphere in order to find methods of overcoming theeffects of ionospheric disturbances.An unusual feature of the polar and subpolar ionospherestems from seasonal variations of the polar atmosphere's solarillumination -- continuous daylight in summer and continuousnight during the winter. A second feature of the ionosphereat high latitudes involves effects on ionization created bycharged solar particles.The main characteristics of the auroral ionosphere are di-versity, variability and abnormality. The auroral ionosphereexhibits a wide variety of disturbed conditions. It resemblesthat in the temperate zones only during quiet conditions and

then only on rare occasions.Perhaps the worst ionospheric condition, from the stand-point of communications is the so-called "polar blackout".During such occurrences, reflections cannot be obtained fromthe ionosphere within the frequency range of ground-based ion-osphere recorders callJd ionosondes. Consequently, the iono-grams or records of electrons versus height obtained are some-times completely blank. Rocket flights have shown that thesepolar blackouts stem from an abnormal increase in the ioniza-tion of a specific ionospheric region -whiich is caused by solarparticles. The effect on communications is a complete cessa-

tion of radio sky-wave transmissions at high frequencies dueto absorption in the D-region.

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This phenomenon is similar to the "sudden ionosphere dis-turbances" which produce abrupt and simultaneous radio fadeoutthroughout the hemisphere which may last from 10 minutes to anhour. Polar blackouts, however, are more gradual in their be-ginning and recovery and last for substantially longer periods-- sometimes continuously during the daylight hours for severalconsecutive days.The "ionospheric storm" is another type of disturbance in-

tensified in the auroral zones. It is characterized by a gen-eral instability of ionospheric conditions, a decrease in themaximum density of ionization and an increase in absorption.The maximum employable frequencies are much lower than normalduring these periods and the restricted communication spectrumis subject to rapid fluctuations in signal intensity. An ion-osphere storm is usually accompanied by a magnetic storm or aperiod of unusual fluctuation in terrestrial magnetic intensity.The topside sounder technique is the only technique knownthat can provide electron-density profiles synoptically abovethe F2 maximum. Such soundings should permit the investigationof the physical properties of the ionosphere as a function oftime and geographical location. The data should be particu-larly valuable since the planned orbital inclination of 80degrees with the Alouette satellite should provide data on thef little known and very complex high-latitude regions (polar and

' auroral zones). The profiles obtained in the equatorial re-gions should be of interest since the distribution near theequator should be materially affected by the earth's magneticfield. (Since the magnetic field at the equator is nearlyhorizontal, vertical diffusion of the charged particles issignificantly inhibited.)In adeition to its scientific value, the increased know-ledge of the ionosphere is directly applicable to communica-tions and tracking applications. The importance of the iono-sphere to terrestrial radio communication is well-known. Pre-dictions of ionospheric storms and disturbances are often un-satisfactory, since these predictions are based on inadequateinformation. Since a thorough understanding of natural phe-nomena is a prerequisite to their intelligent use, a betterknowledge of the entire mechanism should lead to more preciseforecasts.The prediction of maximum usable frequencies for communi-cation purposes presently is based upon observations from

ground-based ionospheric stations (ionosondes). This infor-mation was considered of sufficient importance to justify theestablishment of about 150 ground-based ionospheric sounding

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stations throughout the world. However, this number of stationsis not sufficient for accurate world-wide mapping of the bottom-side ionosphere.Two of the most important observations obtained by thesestations are the height and density of maximum ionization in theionosphere. In principle, several topside sounder satellitesshould provide this information synoptically and with bettergeographical coverage.It is also important to realize that the Ionosphere and thelower atmosphere present severe problems in designing precisiontracking systems. Since the disturbing effects of the loweratmosphere (both refraction and absorption) become significantbefore a frequency is reached where the ionosphere .s completelytransparent, the ionospheric problems cannot be bypassed byraising the operating frequencies. High frequencies have otherdisadvantages, such as the need for complex antennas.

General Instrumentation DesignThe instrumentation designed for the Alouette topside sounderis a miniaturized version of a. onventional bottomside sounder orradiosonde technique. A swept-frequency system was selected inpreference to the simpler, fixed-frequency system to be employedlater in the U. S. S-48 satellite because of the extreme complex-ity of the ionosphere over Canada. The sounder will transmit andreceive pulsed radio frequency signals and the carrier frequency

wrill be swept periodically over the frequency range from 1.6 to11.5 megacycles. The time-delay versus sounding-frequency infor-mation will be transmitted to the ground via telemetry and willbe recorded on magnetic tape. Ionograms will be produced throughsubsequent playback and decoding of the tape at DRTEts centraldata processing fac: ity.An altitude of about 600 miles was chosen for the satellite'ssoundings as a compromise between a variety of requirements.Although the ionosphere extends beyond 1000 km, a substantialportion of the total ionization is contained between 250 km (a'.-titude of maximum ionization) and the 1000 km level.

The Experiments1. The DRB's first exploratory experiment will measure diurnalhour-to-hour changes in the ionosphere dir',ctly bel5ow the sa~eliteat all latitudes.

This primary experiment led to the choice of a polar orjit.The plane of a polar orbit rotates with respect to the earth onlyonce a year, however, so that six months will be required to-14-


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measure the daily variation in the ionosphere above a telemetrystation. By changing the inclination eastward to 750 or 800,the plane of polarization can be made to rotate twice as fast -producing a diurnal variation in three months. Because it wasclearly desirable for the satellite to pass over the geomagneticpole at 78 degrees latitude, the final choice of an inclinationanle at 80 degrees was established.The Alouette will not be able to observe echoes from theionosphere at frequencies below the resonant frequency of the

plasma in which i.t is imbedded. The lowest sounding frequencywas selected therefor-, slightly below two megacycles, as itis probable that the plasma frequency will be between one andt;Jo megacycles, at an altitude of 1000 Rm. The highest frequencyo2 11.5 megacycles wns determined on the basis of the maximumionospheric densities expected when the Alouette experimentswil' be performed.

Associated with the topside sounding measurements of thesignal reflected upwards from the ionosphere will be a ground-based experiment at Resolute Bay wnich will receive the swept-frequency high frequency transmissions that penetrate the iono-sphere to the ground station. The absence of high frequencyinterference and noise levels at the northern Canadian base makeit an ideal location for such an experiment. A digitally con-trolled receiver, especially developed for the purpose, w.illfollow a pre-programmed, nonlinear frequency sweep. Provisionhas been made for rapid and easy modification of the receiverfrequency sweep rate to match changes which may occur in thesatellite sounder sweep rate.2. As the Board's second experiment, an attempt J.ill be madeto determine the electron density at the satellito altituderom a measurement of cosmic no ise.

For this purpose, cosmic noise across the frequency band0.5 to 13 megacycles will be measured. A signal derived fromthe swept-frequency ionospheric receiver automatic gain con-trol circuit will be transmitted via the 1/4 watt telemetrysystem. The frequency at Which cosmic noise disappears willgive the electron density at the satellite.3. Objective of the third experiment will be to listen in thevery low frequency radio spec1rum 1- kilocycles per second)for "whistler" (audio frequency si-gals) signals.

A very low frequency receiver with a pass bank of 1-10kilocycles per second and a gain o1 85 decibles has been in..cluded in the spacecraft instrumentacion.

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The input to the receive r is permanently connected with the150-foot dipole by means of a suitable low-pass filter. Theoutput. normally open, can be connected by means of the commandsystem with the two-watt telemetry system. This signal will beadded to that from the ionospheric sounder's receiver and re-|corded with it at the ground telemetry stations. Subsequently,filters will be used to separate the very low frequency infor-mation from that of the sounder.4. NRcls particle detectors in the sounder payload will measureone othe causative agents onization in the polar ionosphereaFthe same time and place as their effects. This experimentfitL measure particularly, primary cosmic ray particles outsidethe earth7Fs atmosphere including the electrons, protons anda~lpha particles.

The polar orbit permits measurement of changes in particleflux caused by the earth's magnetic field. These measurements jare particularly valuable for auroral studies and in investiga-ting the leakage of particles from the Van Allen belts or mag-netosphere.Space has been made available to NRC within the Alouette forsix detectors which will measure electrons with energy above3,000 electron volts and protons with energy above 500,000 elec-tron volts. Alpha and heavier particles with energies up toseveral billion electron volts will also be measured. The de-tectors are similar types to those carried in the U. S. Explorerand Pioneer satellites.

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V

NASA'S TOPSIDE SOUNDER PROGRAM

Consideration of satellite-borne topside soundingexperiments got under way in 1958. On July 3, 1958, Dr.Lloyd V. Berkner, Chairman of the Space Science Board ofthe National Academy of Sciences, sent out a request forideas on satellite experiments. Several organizationsreplied with proposals for topside sounding experiments.Further support was provided by the Space Science Board'sWorki.ng Group of Satellite Ionosphere Measurements meetingin Boulder, Colorado in September 1958. At a spec'almeeting in October 1958 in Ithaca, New York, called by Dr.Henry Booker to consider the topside sounder experiment indetail, at least seven groups expressed interest in thistype of experiment. In particular, this meeting stimulateda proposal from the Canadian Defe:.se Research TelecommunicationsEstablishment (DRTE), which came to NASA at the end of 1958.NASA was pleased to accept DRTE

ts cooperation on the TopsideSounder program, and it was agreed that this scientificundertaking would be a joint effort between Canada and theUnited States; each country would pay its own costs of theproject. This was the first international, arrangement forcooperative research in a space vehicle. A joint announcementof this arrangement was made simultaneously by both countrieson April 20, 1959.Concurrently, NASA had requested that the Central RadioPropagation Laboratory (CRPL) of the National Bureau ofStandards, Boulder, Colorado, examine the topside sounderproposals received by NASA for scientific merit andengineering feasibility and recommend immediate and long-range approaches for this area of research.In June 1959, a CRPL study report recommended the fixed-frequency system as a first-generation experiment and suggestedthat the DRTE of Ottawa, Canada be encouraged to develop itsswept-frequency system as a secornd-eneration experiment.This second recommendation was, in fact, a concurrence byCRPL with the decision already reached between NASA and DRTE.The topside sounder effort, which began in Canada early in1959, is currently known as Lte Alouette Project.NASA and CRPL discussed the development of the simplerfixed-frequency system as a parallel effort, in view of itscomplementary features. A joint proposal from CRPL andAirborne Inscruments Laboratory (AIL) was received by NASAin January 1960. CRPL was to provide scientific supervisionof a fixed-frequency experiment and analyze the resultingdata, and AIL was to design, constructs and test tile satellite

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payload. The CRPL/AIL topside sounder experiment is knownas the S-48 Topside Sounder Project. Work began at AIL onMay 9, 1960 under a contract letter of intent that providedpartial funding. About a year later, the AIL contract wasfinalized and fully funded. For this program, the expensesof CRPL are paid annually by NASA through a routine interagencytransfer of funds.Since the Alouette and S-48 projects are under the sameproject manager at Goddard Space Flight Center -- Mr. JohnE. Jackson, a senior ionosphere physicist -- and in view ofthe similarity of objectives and techniques in the two projects,a joint working group was set up early in 1960. The UnitedKingdom then expressed an interest in participating in theTopside Sounder program. Under the present agreement, theUnited Kingdom supports the United States program by operatinga telemetry station in the South Atlantic. In return for theuse of this station, the United States provides topside sound-ings over the United Kingdom stations at Winkfield (England)and Singapore. Data from all three United Kingdom stationswill be used in ionospheric research in England.Project S-48 is one of six NASA projects designed tostudy the nature, dynamic behavior, and distribution in timeand space of charged particles in the vicinity of the earth.The objectives of this experiment are similar to those ofthe Alouette. The S-48, however, will emphasize the study ofmeridional cross sections through the ionosphere usingtelemetry stations along the 750 Wmeridian. The UnitedStates system has a low resolution and a fast profileacquisition rate; whereas, the Canadian experiment has ahigh resolution and slow profile acquisition rate. In theS-48, six fixed frequencies will provide downward pulse

transmissions and echo receptions in the 3 to 9 MC range.The S-48 payload, weighing about 105 pounds, is scheduled forlaunch in 1962 by a Scout vehicle into a near circular orbitat an altitude of about 1,000 Ian (620 miles) and with an 80-degree inclination.ROCKET TESTS

Since previous rocket experimentation provided noprecedents for the Topside Sounder program, an importantpart of the CRPL/ATL effort has been rocket testing of asimplified topside sounder. In two firings at NASA'sWallops Island, Goddard scientists proved the feasibilityof topside sounding techniques and information wascontributed to DRTE for the design of Alouette.

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VI

THE SPACECRAFT AND RELATED INFORMATION

The Alouette spacecraft is an oblate spheroid designed asa compromise between two requirements -- first, accessibilityand the easy removal of the electronic packages within, andsecondly, constancy of the effective fraction of the total sur-face area illuminated, a desirable feature for maintaining con-stant solar cell output power.

Electronic components are mounted on a platform on eachside of the central structure which contains the sounding an-tenna modules and batteries. Attached to this structuresperiphery are two half-shell aluminum spinnings which form thesatellitets "skin." The solar cell panels and two heat-controlend caps are fixed to the outer surface of the shell. Thecentral structure is attached to a thrust tube by which theentire load is supported.

The result is a vehicle with mechanical access to solarcells and electronics and an aspect ratio constant to within10 percent. The aspect ratio varies from 3.8 to 4.2 over allpossible orientations of the vehicle relative to the sun.

The spacecraft is 42 inches in diameter and 34 inches inheight. Its total weight is approximately 319 pounds with thefollowing breakdown: PoundsCentral structure including thrust tube 30Spun aluminum. skin and outer structure 31Solar cell panels including cells covered

with 0.012 inch glass 21Sounding antennas plus drive mechanism 45Telemetry antennas 2Electronic package including wiringconnectors 115Nickel-cadmium storage batteries 75Sounding Antenna Design

The sounding antenna 3ystem consists of crossed dipoles,one of which measures 150 feet sip-to-tip and the other, 75feet tip-to-tip. Individual poles, 732 and 36 feet long, are0.90 inches in diameter.A novel design feature of the antenna is the relativelycompact stowage arrangement within the spacecraft. Two antennamodules with the 75-foot poles are wound on storage spools, the

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complete storage unit being about 30 inches long. The antennatubes consist of strips of spring steel 0.004 inch thick andfour inches wide, formed and annealed into circular sectionseach with an over-lapping but open seam. For stowage, the tubesare drawn through a set of guides which force them to open andreturn to the flat strip shape. This is then wound tightly ona storage spool.Two flat, rubber friction-driye belts, each about 1 inchwide and driven by a set of pulleys, pull the spring steel fromthe storage spools during antenna extension. Because the steelantenna strip stored on the spools is not in its stress-freestate, it would normally tend to unwind similar to the unwindingof a clock spring. The rubber drive belts consequently serve asecond purpose in constraining the antenna on its storage drum.The four antenna poles will be extended in unison by a sin-gle motor and gear train. The shorter poles will be declutchedfrom the drive when fully extended while the longer two willcontinue to unwind from the drum. The rate of extension of each

tube is 0.17-foot per second. Antenna poles formed in thisfashion provide the necessary rigidity and at the same time,permit stowage in a. confined space.Space Environment Requirements

The spacecraft temperature is controlled by adjusting theoverall a/e (absorptivity/emissition) ratio, or the ratio ofheat absorbed from the sun and earth to that lost by the sat-ellite into space, This is accomplished by controlling the"color" of the materials on the surface of the spacecraft.A near-spherical spacecraft shape was chosen because of itsconvenience from the standpoint of passive temperature controland constant solar cell illumination aspect. View or shapefactors governing receipt of radiation do not change appreciablywith position in orbit. Because the spacecraft is spin-stabil-ized, radiation will also be averaged conveniently about theouter shell. The spin rate in orbit is predicted to be about2,3 revolutions per minute.The duty cycle is such that the average power consumptionis about 10 watts (35 watts when operating) which must be dis-sipated as heat energy into space. For a 320-pound satellite,

this low rate of power dissipation is acceptable. A designproviding low radiative and conductive coupling between theouter shell and the inner payload, therefore, was consideredmost effective. This design will permit solar cells to operate

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as near 00C as possible in order to gain maximum cell efficiencywhile the inner instrument package and nickel cadmium storagebatteries are held near room temperature at 200C.Radiative isolation of the inner spacecraft from the outershell will be effected by placing a radiation insulator con-sisting of several layers of aluminized mylar, interleaved withunbonded glass paper, on the inner surface of the outer shell.Low conductive coupling of the inner payload to the outer shellhas been achieved through special structural design.The net effect of the overall design will be to reduce.theorbital temperature excursions of the inner payload to substan-tially less than those likely to be encountered by the outershell.It is estimated that the following approximate mean temper-ature will prevail in orbit -- for 100 percent sun, the meanouter shell and :Jnner satellite temperatures will be +280 C and+300 C respectively; for 66 percent sun, the mean outer shelltemperature will lie between -15 C and +100 C, while the innersatellite temperature will be in the range 0 C to +50 C.

OrbitThe Thor-Agena B carrier vehicle will be fired at 80 degreesinclination eastward and the spacecraft will be injected into acircular orbit about the earth at an al';itude of about 600 sta-tute miles,This orbit was selected as the best compromise between apolar orbit with its greater energy requirement and one in whichthe plane appears to precess at a high rate. A low precessionrate for the orbit's plane was selected to maximize the collec-

tion of data which will show diurnal variations at each telem-etry station location.Because the desired thermal environment heavily influencesthe choice of a launch time, an analysis was made to determinethe percent sunlight versus time after launch for any given dayin the year. This analysis indicated that the best compromisebetween moderate solar heating in orbit at the outset and solarheating during the pre-injection coast phase was a launch intothe proposed orbit at about 2300 hours Pacific Standard Time.

Satellite DynamicsWith antennas fully extended when in orbit, it is estimatedthe spacecraft spin rate about its maximum angular momentum axis

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will be 2.3 revolutions per minute initially. Because the sounder'will not observe echoes if the satellite stops spinning anddrifts into a position where an antenna null points down into theionosphere; a spin decay study leas made to assess the probabilityof this occurrence. Calculations, which consider energy lossesdue to electromagnetic induction and magnetic hysteresis, showthat the spin decay half-life will be approximately seven years.The Sounder

The sounder transmits pulsed radio frequency signals cover-ing the frequency range from 1.6 to 11.5 megacycles per second.A 100 microsecond pulse is repeated at a rate of 67 pulses persecond and the rate of frequency sweep is approximately one mega-cycle per second. A variable frequency oscillator (VFO) sweep-ing from 19,5 to 32 megacycles per second is mixed with a 19megacycle per second fixed frequency oscillator to produce therequired frequency sweep. It is desired to operate the sounder'sreceived over the frequency range 0.5 to 13 megacycles per sec-ond even though the antenna matching networks are efficient onlyover the frequency range 1.6 to 11.5 megacycles per second. Thisdifference is necessary to provide for the reception of cosmicnoise over an extended frequency range. The increased cosmicnoise intensity at the low-frequency end of the spectrum willoffset partially the decrease in the overall sensitivity of thereceiving system.The received signal from the antenna matching network ismixed again with the VFO output to produce a frequency of approx-imately 19 megacycles per second. This is amplified in a 19megacycles per second intermediate frequency amplifies with abandwidth of 120 kilocycles per second in order to raise thesignal level well above the noise level of the next mixer. A500 kilocycles per second amplifier having a log-linear ampli-

tude response and a bandwidth of 30 kilocycles per second followsthe second mixer and an envelope detector provides the wide bandtelemetry output.Transmitter

The low level stages of the transmitter are wideband trans-former-coupled amplifiers with the final amplifier consisting offour class A pairs in push-pull parallel. Power consumption is4.3 watts, the overall power gain is 46 decibels, and the powergain of the final stage is seven decibels,Antenna Matching

Each of the two sounder antennas is driven via an appropri-ate matching network with the low frequency network effective

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over the range 1.6 to 4.5 megacycles per second and the highfrequency network over the range 4.5.to 11.5 megacycles persecond. These networks are driven in parallel from a singlepower amplifier and operate as a crossover device directingthe amplifier output power to the appropriate antenna as thefrequency changes.Transmitters

Two telemetry transmitters will be employed, one opera-ting at a power level of 0.25 watts at a frequency of 136.590megacycles per second and a second transmitter with a poweroutput of 2.0 watts at a frequency of 136.080 megacycles persecond. Both transmitters will be operated only on commandto conserve battery power. The lower power transmitter is somodulated that it may be used as a tracking beacon in anemergency. Both transmitters are duplicated in order that aspare unit may be switched in, on command, in case of failure.Antenna

The telemetry antenna consists of four whips in a turn-stile configuration which are drivexi by a hybrid ring isolator.This antenna is shared by the two telemetry transmitters andby the two command receivers.Tracking Beacon

A 50 milliwatt, 136.980 megacycles per second trackingbeacon transmitter has been provided for use by the NASA Mini-track network. This transmitter is unmodulated and radiatescontinuously via a single 4 wavelength whip mounted on the topof the satellite.Ground Complex

Satellite command and telemetry receiving and data record-ing stations will be operated at the following locations:Resolute Bay, North West Territories )Prince Albert, Saskatchewan Canada - DRTEOttawa, Ontario StationsSt. Johns, Newfoundland, CanadaCollege, AlaskaGrand Forks, North Dak-ta (on request) NASA MinitrackFort Meyers, Florida StationsQuito, Ecuador

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Antofagasta, Chile )Winkfield, England NASA MinitrackWoomera, Australia Stations (cont.)SingaporeSouth Atlantic Station ) British StationsThe Canadian and British stations and NASA's Minitrack facil-ities will be provided with command capability and all the infor-

mation received at each ground station will be recorded on 2- inchmagnetic tape in seven channels.At Resolute Bay only, the "direct-through" experiment will beconducted by synchronizing a high frequency receiver on the groundto the frequency sweep taking place in the satellite via the telem-etry link.Look-angles for each pass at a ground station will be computedon a 30-second time interval by NASA. Distribution of this infor-mation to the Canadian stations will be the responsibility of DRTE.

Data ProcessingThe DRTE data center at Ottawa will process tapes from thetelemetry receiving stations. To permit this to be done in aneight-hour day, tapes will be replayed at double speed.The tapes will contain three main signals:(1) The ionosonde receiver output (the "video" signal),together with line and frame sync signals.(2) The four subcarrier signals carrying the "house-keeping" information, cosmic particle experiments

and cosmic noise.(3) The time code track which will be a one kilocycleper second carrier amplitude and width modulatedin accordance with the NASA 100 pulses per second36 36 bit time code format. In addition, voice an-nouncements or the date, time, and station identi-fication will be carried on one of the tracks,but ahead of the telemetry information.The output of the tape replay units will be processed byusing standard subcarrier discriminators and decommutators andwill provide ionospheric high frequency records ("B" scans) on35 mm film, using a 24 mm x 36 mm format and displaying time on

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a strip parallel to the film's edge in a binary coded decimalform. The "straight-through" high frequency signal, to berecorded at Resolute Bay only, will be made into "A' and "B"scans when required. The "A" scan is the plot of amplitudeversus time for each pulse.The data obtained from NRC's particle counter experiments,together with the time code, will be recorded on ar 8-channelpen recorder and after integration, will also be punched on IBMIcards.Tracking Sequence

The Pacific Hissile Range will track taie Thor-Agena B launchvehicle from lift-off, using four radars each having 12 footdiameter antenna. Two of the radars are at Pt. Arguello, Califor-nia, one is at Pt. Mugu, California, and the other is located onSan Nicolas Island, California. These radars will either "skin"track or interrogate the vehicle's "C' Band Beacon for range dataThe radars at Pt. Arguello and Pt. Mugu Will track the launchvehicle until loss of signal over the radio frequency horizon.

The radar on San Nicolas Island will track the Agena B through itsfirst burn period and slightly beyond, if posS;ible. Present pre-dictions indicate that the Agena B will be down to an elevationangle of about 3 degrees above the horizon and approximately 1168kilometers down-range from San Nicolas when the first burn periodof the Agena B is completed. If the Range Tracker ship used inProject Mercury can be made available for the Alouette mission,the ship will be placed in a position down-range so that trackingdata can be obtained during the ending of the Agena B first burnperiod and for a short period afterwards.PMR will obtain tracking data from the radar sites in theform of time, range, azimuth, and elevation and will computefirst injection conditions (at the end of the first Agena B burnperiod) and forward them to Atlantic Missile Range and GoddardSpace Flight Center.After the first burn injection conditions are received atAMR they will be forwarded to the ANR station at Pretoria,South Africa and used in computing iook-angles for that station.Goddard will use the first burn injection conditions for rawradar data and for subsequent computation of non-nominal orbitalelements and prediction information if needed.Goddard will forward to ATIR a copy of the Goddard-compuredinjection parameters if they can be computed in sufficient tLiceto be of value for predicting acquisition data for the Pretoriastation.

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AI4R will track the Agena B during its second burn,period --from 60 seconds prior to second ignition to the end of the secondburn period plus 60 seconds -- using a radar having a 12 footdiameter antenna located at Pretoria, South Africa, This radarwill be performing at the limits of its range alid elevation butwill be backed-up by a 60 foot diameter parabolic antenna locatedin the same area. The raw radar rata will be used at Pretoriato compute the final injection co1xlitaons. The raw radar dataand other injection conditions will be forwarded front Pretoria toAMR for computation of new orbital elements and acquisition datafor the College, Alaska Minitrack Station. This data also tlllbe relayed to Goddard and PMR.

AMR will also obtain vehicle and spacecraft telemetry byvoice link from the AMR ship to Pretoria and/or from Pretoriadirect by voice to AMR. AMR wi in turn, relay quick-look andother information by voice to PM, .nd the GSFC Mission DirectortsCenter there.Supporting and Auxiliary Experiments

Cosmic Noise Measurement in Transit IIA2arly in the Alouebte system design it was realized that anaccurate determinatlin of cosmic noise power level at an altitudeof 1000 km was de*Iroble.Through the cooperation of the Applied Physics Laboratoryof Johlns Hopkins University, DRTE installed suitable measuringequipment in the Transit IIA spacecraft launched into orbit onJune 22, 1960. A 3.8 megacycles per second receiver with anautomatic gain control voltage, having a time constant of 0.lsecond was used to measure cosmic noise levels,. Ferrite loopantennas became part of the Transit IIA despin weights. The ex-periment was designed to operate for one week. PEcellent telem-

etry records were obtained. The noise at 3.8 megacycles persecond as measured in the northern hemisphere, indicated approx-imately 2 microvolt per meter equivalent broadside polarizedfipld strength in a 40 kilocycle bandwidth, or approximatelyJ09 degrees Kelvin brightness temperature.ALtena lfcation Experimentase3)

Because the physically long sounding antennas are of noveldesign and could not be tested completely on the ground, DRTEcarrted out an expe3riment to test them in a space environment.o ~ntenna modules, each containing 75 foot poles, were mountedit a Javelin rocket nosecone provided by NAB.!;

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The launching took place on June 14. 1961, at NASAIsWallops Island, Virginia Station at 8:03 EST. The plannedtrajectory wras achieved and the payload reached an altitudeof 900 Im. The fairing was ejected arnd antenna extensioninitiated at approximately 100 miles altituue. This NASAfiring demonstrated the feasibility of the topside soundingtechnique under consideration for tI'e satellite and provedalso, the feasibility of the antenna system design., Thetest was not completely successful as two malfunctionsoccurred. The primary mission, however, was considered tohave been accomplished when records showed one pole extendedto its full 75 feet while the other attained 50 feet.

Vehicle performance was normal with the nosecone spinrate approximately 570 revolutions per minute at the end offourth stage burnout. Fairing ejection and despin occurred122 seconds after launch but then despin was more effectivethan intended -- to 10 instead of the desired 135 revolutionsper minute. The increased stress due to the very high tangen-tial deceleration is believed to have caused some deformationof the extension mechanism of one antenna, thereby partiallyimpeding its performance. The other antenna withstood thedespin and apparently functioned normally, Antenna impedancemeasurements correlated with potentiometer indications of theextended length showed no evidence of distortion or bucklingof the antenna poles. The extended length weas used as dipolelength to compute theoretical free space inpedance. The im-pedance measured in the payload wras writhin two percent of thisvalue.

The electrical impedance of the antenna descending throughthe ionosphere was measured at 14 megacycles per second. 'hismeasurement wlas also to be performed a. 14megacycles per secondwhich is in the operating frequency range for the S-27 sounder.The failure of a timer, however, prevented the switch-over ofthe radio frequency drive from 14 to 4 megacycles per secondfor the antenna. The measurement showed a departure fromsimple theoretical predictions but not sufficient to cause con-cern about the design of the antenna system.

The mechanical fault whichl is assumried to have caused onepol.e to stop at [ fret was duplicatec in hl lalc av'ory aildan improved drivc mecinanism, us.ng p'' -iali,; Clef;icnCu t.:i''drivc belts, eliminated the fault.

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VII

TIHjE CANADIAN DEFENCE RESEARCH BOARD

Defence science as a formally organized activity in Canadabegan April 1, 1947, with the formation of the Defence ResearchBoard. Although created as an integral par', of the Departmentof' National Defence, the Board is civilian directed and staffed.T1hor this reason, it is believed to be unique among the nationsof the western world.

.the Board's guiding policy is specialization on research ofiimportance to Canada or for which Canada has unique resources orfacilities.Amcng its basic responsibilities is the encouragement ofresearch within the universities and through other agencies.Fundamental research is playing an increasingly importantrole in the Board's overall program and DRB scientists have woninternational recognition for their basic research contributions

in a number of fields - particularly i.) pper atmosphere inves-tigations.The topside sounder satellite project is a natural exten-sion of nearly 15 years of investigations by ground-basedfacilities and by instrumented research rocket nose cones of theupper atmosphei-e with particular empnasis on tne effects of theaurora borealis on the ionospheric regions.

DRB'sDRB's annual budget, now approximately `32,OO0,OOO. coversthe operations of its Headquarters and eignt establi3hments andmeets the costs of advisory committees, panels and consultants.This budget also finances an extramural grants and contractsprogram in Canadian universities and industry approximating$3,000,000.

Dr. A. Hi. Zimmerman assumed the cha-.rmanship of the DefenceResearch Board on March 1, 1956.Th.3 Chairman of The Defence Research Board

lBorn in Hamilton, Ont., in 1902, A. 1I. Zinuriernan, ODE, B.A.Sc., LL.D., attended Royal Military College in Kingston, Ont.,where hie was a Silver Medallist, and the University of Toronto,where he was awarded a B.A.Sc. in mining engineering in 192)1.

For six years, he was engaged in Mining engineerin, innorlt'ern Ontario, Quebec, and In the western United States. In


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1930, Dr. Zimmerman returned to eastern Canada, where he joinedthe Moore Corporation in Toronto. From 1932 to 1954, he heldvarious positions at the Company's Niagara Falls plant in NewYork State including that of General Production Manager forMoore Business Forms, Inc. During the same period, he servedthe Canadian Government in a senior capacity when Canada wasengaged in World War II and in the Korean war.The Chairmants close association with the Defence Research

Board stems from 1951 when he was named a Board Member. InJanuary, 1955, he was appointed Vice-Chairman and on March 1,1956, became the Chairman of the Board.THE DEFENCE RESEARCH TELECOMMUNICATIONS ESTABLISHMENT

The Defence Research Telecommunications Establishment, atShirley Bay near Ottawa and which consists of the Radio Physics,Electronics and Communications laboratories and the PrinceAlbert Radar Laboratory in Saskatchewan, began as a small groupin 1941 to investigate radio propagation problems. Within sixyears, the unit had broadened its activities to include auroralresearch and an increasingly expanding area of telecommunica-tion investigations.The Defence Research Board was established in 1947 and thegroup became one of the Board's first research stations. Itbecame known as the Radio Propagation Laboratory.In 1950, its responsibilities were expanded, additionalpersonnel were recruited and the Electronics Laboratory wasadded to form the Defenne Research Telecommanications Establish-ment. Six years later, DRTE was reorganized into three scien-tific wings, the Radio Physics, Electronics and a new Communi-cations laboratory.Scientific and technical personnel from the Communicationsand Radio Physics units in 1959 began operation of the PrinceAlbert Radar Laboratory, physically almost a twin of the U. S.Millstone Hill facility in Massachusetts.

RPLRPL particularly concerns itself with radio propagationproblems, and in particular, with those associated with northernlatitudes where the aurora and other natural disturbances com-plicate radio communications.

ELTne Electronics Laboratcv;. -s been responsible for tnedesign and fabrication of the .-27 satellite and specializes in

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electronic techniques as applied to a variety of communicationsand r'lated projects.EL has made major contributions to the miniaturization of

equip,,aent through the use of transistors, light-weight materialsand other techniques. These special interests have been partic-.ularliv helpful in the design and fabrication of specific comr-punenzs for the S-27 satellite.CL

CL specializes in research on radar and communicationssystems with the aim of increasing their reliability and useful-ness -underdifficulties likely to be presented during modernvrdrf are.Chief' Superintendent, Defence Researcn TelecommunicationsEstablishment

crank T. Davies was born in 1904 in Glamorgan, South Wales.He studied physics at the University College of Wales, Aberys-twyth, and in 1925 came to Canada, where he was associated withtht oiMversity of Saskatchewan as a lecturer in mathematics anda demonstrator in physics.

-Ar. Davies then moved to McGill University where he ob-tained His Master's degree in 1928. During this period he wasa demonstrator in physics.lie spent the next two years as a physicist with AdmiralByrd during tfLa celebrated explorer's first Antarctic expedi-ticii during 1)28-30. In 1930, he joined the staff of theDepartment of Terrestrial Magnetism of the Carnegie Institute

Do' W4ashirngton where he remained for almost ten years. From1932 to 193)4, Mr. Davies was on. furlough to the Canadian Mete-.:,r-:-;ical Service in command of the Canadian Second Polar YOarexoedlitlon at Ches oerf4eld Inlet, Northwest Territories.

cv,.een 1936 and 1939, he was director of the GeophysicsO)3sorvatory of the Carnegie Institute of liuancayo, Peru, asclon;tific research center located at an a:titude of -1,000feet in the Andes mountains. After a further tw' years inSoutin America, Mr. Daviecs spent a Short period with the Nation-al Research Council of Canada as a liaison officei.in 1946, he joined the Defence Research Board staff., and

becc(,.;u Superintendent of the Radio Physics Laboratory, Ottawa,in Ic.hn 1951 he wraS made Superintendent- of the Defenceh nezeach Tciecommunications Establishnenrt. In the summer of

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1955, Mr. Davies was namied Assistant Chief Scientist and inaddition, Director of Physical Research at DIUIeadquarters.in 1958, he assumed full-time duties as Assistant ChiefScientist (Systems), as the loard's activities in this fieldincreased. The following year, he returned to DRTZ as ChiefSuperintendent.Among the honors awarded Mr. Davies are the U. S. Ant-arctic i';edal in 1930, and fellowships in 1943 in the RoyalSocJety of Canada and the Arctic Institute of North America.

I:e has published scientific papers on aurora geomagnetismand radio propagation.

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alouette s-27 press kit

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