anik-d press kit

8/7/2019 Anik-D Press Kit

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1\15/\New'sNational Aeronautics an dSpace AdministrationWashington, D.C. 20546AC 202 755-8370

Dick McCormack ForReleaseHeadquarters, Washington, D.C. IMMEDIATE(Phones 202/755-8104)Debra RahnHeadquarters, Mashington, D.C.(Phone.: 202/755-3897)Jim LacyGoddard Space Flight Center. Greenbelt, Md.(Phone: 30J./.34.4-8955)..ELEASE No)t 82-126

NASA TO LAUNCH CANADIAN SATELLITEA Canadian domestic communications satellite, Ani.k-D, is

scheduled for launch by NASA from Cape Canaveral, Fla.., no ear-lier than Aug. 26 with a launchmwindow from 7:22 to 9:43 p.m. EDr.

This is Canada's .10th.satell-ite and the fifth spacecraft ina series of domestic commercial communications satellites ownedand operated by Telesat Canada. Trhe spacecraft will be placedinto a geosynchronous orbit to provide communica.tAons coverageover Canada, the second largest.nation in area in the world.

The spacecraft -will be positioned at 104 degrees west lonqi-tude within 30 days after launch and will be used by Telesat asan in-orbit replacemerit/backup for the three aging Anik-A (1972,1973, 19/5) and Anik-B (1978) satellites.

August 23, 1982

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The Telesat payload for-this Delta 3920 launchAincl.udes aMcDcnnel.l Douglas built Payload Assist Module and the Anik-Dspacecraft. A payload attach fitting, a solid rocket motor and aspin table are the major elements of the Payload Assist Modulesystem. The Spinning Solid Rocket .Motor is used to propel theAnik-D space.craft into a elliptical transfer orbit from the park-Ing orbit provided by the Delta 3920. Stabilization of the pay-load is accomplished by spinning the Payload Assist Module-andspacecraft to a 50 rpm.

The Anik-D spacecraft is a synchronous altitude geosta-tionary satellite designed to operate over a .10-year life span.The spacecraft is integra-ted-and tested by Spar Aerospace forTelesat and carries a 24-channel communications payload.

The two main elements of the spacecraft are the spinningrotor, comprising 70 percent of the on-station vehicle weight,and the despun earth-oriented platform containing the communica-tion repeater and its antenna.

A rotating interface, consisting of ball bearings and slip-rings,. permi.ts signa.l transfers to take place and, affords anelectrical path over which power from the solar panels and bat-teries can flow to the repeater payload.

The overall spacecraft length, at launch, is 2.8 meters (112inches); its maximum diameter is 2.17 m (85.33 in.). Afterantenna deployment and extension of one solar panel cylinder, theoverall spacecraft length is 6.7 m (265 in.).

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LAUNCH ,VEHICLEThis is the second launch of the NASA Delta 3920 launchvehicle, and the first launch of .this. version trom the. EasternSpace and Missile Center. The. first' launch was Landsat 4 from

the Western Space and .M^issile Center on July 16, 1982.The Delta Model -3920 straight-eight. configured launch vehicleconsists of an extended long tank Thor first stage with an .RS-2.7engine augmented with nine Castor IV solid rocket motors, a newsecond stage powered by an Aerojet AJ10-1 18K engine, and a 2.4 .m.(96-in.) diameter spacecraft fairing.McDonnell -Douglas Astronautics Corp., Hiuntington Beach,Calif., is the prime contractor for production and launch of theDelta launch vehicle. The company developed and. made availablecommercially the Payload Assist Module 4PAM-D) which takes theplace of Delta's third stage and is considered part of the pay-

load on the Anik-D launch. A Thiokol Star 48 propellant motor isthe propulsion system for PAM-D. .Thiokol also produces the Star30 motor used as an apogee kic.k motor, mounted inside the space-craft itself to inject the spacecraft into a geostationary orbit.Trajectory for the Anik-D spacecraft mission covers theperiod from liftoff to first apogee.of the transfer orbit.At 1,259 seconds into the mission the .PAM-D motor is ignited.An 86-second burn places the satellite into a geostationary trans-fer orbit. The orbit parameters at.third stage engine cutorf(TECO) are as followst apogee attitude (integrated), 36,342 kilo-meters (19,623 nautical mi.les)5 perigee altitude, 185 km (.100

n.mi.)l argument of perigee. 178 degreest and inclination, 24.5degrees.FLIGHT PLAN

-At liftoff six Castor IV solid rocket motors are ignited onthe launch pad and complete their burn at 57 seconds. At 62 sec-onds -the remaining three Castor IV solid rocket motors are ignitedwith their burnout occur.ing a.t 1.19 seconds. The first set of sixground ignited solid- motors are Jettisoned in groups of three .at70 and 71 .seconds with the final set of three solids jettisoned atat 122 seconds. .Main.engine cutoff occurs at.224 seconds. Firststage separation occurs at 232 seconds with the spacecraft fairingjettisoned at 245 seconds.At second state cutoff (SECO), .672 seconds, the vehicle isinjected into an elliptic 225 by 187 km ( 121.6 by 101.1 n.mi.)transfer orbit designed-to provide a 185 km (100 n.mi.) altitudenear the equator. Following SECO), pitch and yaw commands are exe-cuted by the Delta vehicle to provide the r'equired burn attitudefor the PAM-D third stage. The seconds prior to stage 11-IIIseparation, the.third stage is spun up to 50 rpm.

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Xith the separation of -the payload *thWrd stage (PAM) andspacecraft) from the second stage, NASAAD6lta responsibilities are.concluded. Payload Assist Module ignition occurs &t .1,297. secondsand burn~s fo r 86 seconds placing -the payload into the specifiedgeostationary transfer orbit.ANIK-D SPACECRAFT MISSION TRAJECTORY MARK EVENTS

EVENT .TIME (SECStage I Liftoff 0Six Solid Motors Burnout 57Three Solid Xotors Ignition 62Jettison Three Solid Motor Casings 70-Jettison Three Solid Xotor Casings * 71Three Solid Ao.tor.s Burnout 1.19.Jettison Three Solid.Motor Casings 122Main Engine Cutoff 224Ner.nler Engine Cutoff .230Stage I-II Separation 232Jettison Fairing 245..econd Engine Cutoff Command .. 672Final Cutoff Stage II .672Start Stage III Ignition Time Delay Relay 1,257Fire Spin .Rockets .1,257Jettison Stage II 1,259Stage III Ignition .1,297Stage III Burnout 1,383Jettison Stage III J,497First Apogee 20,628

A second stage depletion burn is required for the-Telesat/Anik-D mission.

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Prior to, ngine restart, the second s~tage is reoriented -toan attitrudeiWhich precludes the possibility of stage deorbit.The

decision was made to orient the stage such that .thewreiningpulsive velocity would cause the minimum increase to orbit energylevel (that is, the increase in apogee and perigee altitudes)

andthe maximum reduction in orbit inclination

angle. 1A chane i.norbit nodal angle wi-ll also occur.) The stage centerline will beoriented at restart to be approximately 80 degrees to the velcvcity vector. Achievement of this attitude requires .a roll-pitchmaneuver with the attitude rates applied serially. Restart willbe initi3ted at 4,700 seconds. The second stage will burn to

nom-.inal propellant depletion J7.4 seconds later and will provide

.Animpulsive velocity of 574,.m (1,884.2 feet-) per second. -A equenceof events for the depletion burn is presented in the table below.The orbit characteristics at initiation and completion

of the de-pletion burn are as fol.lows'

NOMINALIGNITION BURNNOUT

Apogee Altitude (km and n.ml.) 218 (117.8) 5-36 (289.6)

Perigee Altitude (km and n.mi.) 195 1105.5) 218 (117.7)

Inclination (degrees) 28.9.6 26.14l7Argument ot.Perigee (degrees) .184.89 53.33

SECOND STAGE DEP.LETION BURNTRAJECTORY

SEQUENCE OF EVENTS AND.CONTROL PRO(GRAM

EVENT TIME (SEC.)

Stage II-III Separation 1,288

Begin Coast Phase Roll Program 4,.190(Roll -Rate = 0.55896 Deg/Sec)End Coast Phase Roll Program 4.340

Begin Second Coast Phase Pitch Rate .4,350(Pitch Rate = 0.56690 Deg/Sec.)End Coast Phase Pitch Program 4,550

Restart-Stage II 4,700

Start of Steady State Burn 4,700

Final Cutoff - Stage II (SECO 2.) 4,71.7

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NASA/TELESAT TEAM

NASA HEADQUARTERSLt.Gen. J.A. Abrahamson Associate Adminlstra.tor forSpace FlightJoseph B. Xahon Dlrector, Expendable LaunchVehicwle ProgramPeter Eaton Program.Manager, Del-ta.H. .. Smy.lie Associate Administrator fo r

Space Tracking and Data SystemsGODDARD SPACE FLIGHT CENTERNoel . 'Hi.nners Director.WilliamC. Keathley Director, Project ManagementDavid fl. Grimes Delta Project.Manager.William R. Russell Deputy Delta Project Manager

TechnicalJohn D. Kr.aft Manager, Delta MissionAnalysis and Integration.Warner H. Hord Telesat Mission Integration

.ManagerRobert I. Seiders Mission Operations and NetworkS.upport ManagerRay Mazur -Mission SupportKENNED'(.SPACE CENTERRichard G. -Smith D.irector

F. Page Deputy Direc~tor|@zhomas S..Walton Director, Caro operationsCharles D. Gay Director, Expendable VehiclesOperationsWayne L. McCall Chief, Delta OperationsJim Weir Acting Chief, AutomatedPayloeds DivisionGayle Hager Spacecraft Coordinator

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TELESAT CANADAEloon Thompson JPresidantWilliam .Zatychec Director-, Satellite SystemsDivisionDave Griffiths Manager, Launch ServicesJohn Korda Space Managers Anlk-.DRay. Miles Ran4e .Coordinator.. .Anlk-D

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(Index: 9, 20, 21, 29)

anik-d press kit

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