Indian National Satellite System-1 Press Kit

8/7/2019 Indian National Satellite System-1 Press Kit

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Its orbital location will be 74 degrees east longitude abovethe Earth's equator. A sister spacecraft INSAT-1, scheduled fora July 1983 launch on Space Shuttle, will occupy a similarequatorial location at 94 degrees east longitude.

Both spacecraft are built by Ford Aerospace andCommunications Corp. under a joint venture of the Department ofSpace, the Posts and Telegraphs Department (P&m) of the Ministryof Communications, the India Meteorological Department of theMinistry of Tourism and Civi]. Aviation and Doordarshan of theMinistry of Information and Broadcasting.

INSAT (lA and 11) spacecraft are designed to provide thefollowing services over a seven year orbital lifetime:

Twelve transponders operating in 5935-6425 MHz (Earth-to-satellite), 3710-4200 MHz (satellite-to-Earth). Used for thickroute, thin route and remote area communication and TV programdistribution.

Two transponders operating in 5855-5935 MHz (Earth-to-satellite) and 2555-2635 MHz (satellite-to-Earth). Used fordirect television broadcasting to augmented, low-cost communitytelevision sets in rural areas, radio program distribution,national television networkinq and disaster warning.

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Weather

A very High Resolution Radiometer (VHRR) instrument withvisible (0.55-0.75 micron) and infra-red (10.5-12.5 micron)channels has resolutions of 2.75 kilometers (1.5 miles) and 11 km(6 mi.) respectively with full Earth coverage; full frame imageevery 30 minutes. Utilization for round-the-clock, half-hourlysynoptic observations of weather systems including cyclones overIndia and the adjoining land and sea areas, sea surface andcloud-top temperatures, water bodies and snow-mapping, etc.

The meteorological component of the system will provide:

Round-the-clock, half-hourly, synoptic observations ofweather systems including cyclones, sea-surface and cloud-toptemperatures, water bodies, snow cover, etc., mapping the entireterritory of India as well as adjoining sea and land areas.

Collection and transmission of meteorological,hydrological and oceanographic data from unattended remoteautomatic data collection platforms (DCPs) to a central dataprocessing center.

Timely warning of impending disasters from cyclones,floods, etc., and dissemination of meteorological information foragricultural and other purposes. Using the INSA" televisioncapability, the warnings can directly reach the population in theareas likely to be affected.

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Data

A data channel for relay of meteorological, hydrological andoceanographic data from unattended land and ocean-based datacollection transmission platforms.Telecommunications

T'he telecommunications component will provide over 8,000two-way long distance telephone circuits potentially accessiblefrom any part of India.Television

The television component of the INSAT-1 system can provide:

. Direct television broadcasting to augmented communitytelevision receivers in rural areas for which direct televisionbroadcast coverage has been identified as more economical.

* Nationwide television coverage in one step.. National networking of terrestrial television

transmitters.

. Radio program distribution.

The INSAT-1 satellites are three-axis stabilized with aprecision attitude control system. They are desiqned to becompatible for launch with unmanned, conventional, expendableDelta 3910/PAM launchers as well as with the manned, reusableSpace Transportation System (STS--Space Shuttle).

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The Master Control Facility for INSAT-1 satellite orbitraising and on-orbit control and management is being establishedin the Hassan District of Karnataka.Telecommunications Ground Segment

The initial INSAT-1 Telecommunications Ground Segmentincludes the following:

* Five large Earth stations.

* Thirteen medium Earth stations.

Eleven remote area terminals.

One road transportable terminal.

Two jeep-transportable/air-liftable emergencycommunication terminals.

* A Network Operations Control Center (NOCC) forcoordination and control of all 6/4 GHz utilization Earthstations.

* Four of the five large Earth stations linked with mainswitching centers of the national telecommunications plants(Bombay, Calcutta, Delhi and Madras) will have a second antennasystem with associated electronics for simultaneous utilizationof INSAT-lA and INSAT-lB satellites.

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Meteorological Ground Segment

The INSAT-1 meteorological ground segment facilitiesinclude:

* A Meteorological Data Utilization Center (MDUC) at NewDelhi for processing INSAT-l VHPR and data collection platformdata which will be received at the Delhi Farth Station of P&T andtransmitted to the meteorological center realtime over amicrowave link.

* Secondary Data Utilization Centers (SDUC) located invarious forecasting offices of the India MeteorologicalDepartment (IMD) will receive processed images from theMeteorological Data Utilization Center over telecommunicationslines (including INSAT-1 circuits).

* About 100 data collection platforms deployed all over thecountry, including some over oceans, and disaster warningfacility.

* The Meteorological Data Utilization Center shall havefacilities for processing, analysis and storage of INSAT-1 VeryHigh Resolution Radiometer and Data Collection Platform data.Each Data Collection Platform shall be capable of handling 10sensors. The primary meteorological. sensorE associated with theplatforms are: air temperature, wet bulb temperature andrelative humidity, wind speed, wind direction, atmosphericpressure, platform housing temperature, rainfall, sunshine andsea surface temperature.

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LAUNCH VEHICLE

NASA's Delta 3910 launch vehicle is 35 meters (116 feet)

high and consists of a 2.4-m (8-ft.) diameter first stage,powered by a Rocketdyne RS-27 liquid-fueled engine; nine ThiokolCastor IV strap-on solid motors; a 1.5-m (5-ft.) diameter secondstage powered by a TRW TR-201 liquid fueled engine; and a 2.4-m(8-ft.) diameter fairing.

McDonnell Douglas Astronautics Corp., Huntington Reach,Calif., is the prime contractor for production and launch of theDelta launch vehicle. The company developed and made availablecommercially the Payload Assist Module (PAM-D) which takes theplace of Delta's third stage and is considered part of thepayload on the INSAT-1 launch. A Thiokol Star 48 solid fuelmotor is the propulsion system for PAM-D. The apogee kick motor(AKM), mounted inside the spacecraft itself, is a liquid fueledMarquardt R.4D-l1 motor.

Trajector for the INSAT-lA spacecraft mission covers theperiod from liftoff to first apogee of the transfer orbit.

At 1,165 seconds into the mission and at an altitude of 190km (102.4 n. mi.), the payload assist module motor is ignited.An 86.37 second burn places the satellite into a geostationarytransfer orbit. The orbit parameters at TECO are as follows:

Apogee Altitude (Integrated) 35,786 km (19,323 n.mi.)

Perigee Altitude 167 km (90 n.mi.)

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Argument of Perigee 179 degrees

Inclination 28.4 degreesFlight Plan

At liftoff six Castor IVr solid rocket motors are ignited onthe launch pad and burn out at 56.95 seconds. At 62 seconds theremaining three Castor IV solid rocket motors are ignited andburn out at 119.150 seconds. The six ground lite solid motorsare jettisoned in groups of three at 70 and 71 seconds with thefinal set of three solids jettisoned at 125.5 seconds. Firststage separation occurs at 231.824 seconds with the spacecraftfairing jettisoned at 241 seconds.

At second stage cutoff (SECO), the vehicle is at an altitudeof 250 km (134.9 n.mi.) and on an impacting trajectory with anapogee of approximately 255 km (137.5 n.mi.). Following cutoff,pitch and yaw commands are executed by the Delta vehicle toprovide the required burn attitude for the payload assist modulestage. One hundred eighteen seconds prior to stage II-IIIseparation, a low thrust ullage is performed to settle the liquidpropellant of the apogee kick motor of the spacecraft. Twoseconds prior to stage II-III separation the third stage is spunup to 40 rpm. With the separation of the payload (third stage(PAM) and spacecraft) from the second stage, NASA/Deltaresponsibilities are concluded. Payload Assist Module ignitionoccurs at 1,165 seconds and burns for R6.37 seconds placing thepayload into a geostationary transfer orbit.

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After transfer orbit injection the spacecraft/payload assistmodule combination tumbles for about 20 minutes, reaching astable spin condition. Spacecraft/payload assist moduleseparation is done by ground command, followed by despin andattitude acquisition to Sun pointing mode, with a roll rate of-0.75 degrees/second.

During transfer orbit operations the spacecraft remains inSun-pointing mode. About two hours prior to first apogee, thespacecraft is reoriented to apogee kick motor firing attitudewith three-axis control, and orientation trim corrections aremade prior to the first firing on the first apogee.

After completion of first apogee kick motor firing, thespacecraft spends two revolutions in an intermediate orbit inSun-pointing mode attitude. About one hour before the second

apogee kick motor firing, the spacecraft is reoriented to firingattitude with three-axis control. The second apogee kick motorfiring is targeted to put the spacecraft nominally on-station.

After the second firing, the spacecraft is reoriented toachieve the normal on-orbit three-axis attitude and stationacquisition orbit maneuvers are initiated. The target stationlongitude is 74 degrees east. This is attained, with dispersioncorrection burns, about 36 hours after second apogee kick motorfiring.

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After station acquisition, the spacecraft undergoes fulldeployment and then commences its geosynchronous phase ofoperations.

The INSAT-lA launch, aboard Delta 161, will be from Pad A ofNASA's Complex 17, Cape Canaveral Air Force Station, Fla.

The first stage of the Delta rocket and the interstageadapter were erected on Pad A on Feb. 27 The nine solid straponCastor IV rocket motors were erected on March 1, 2 and 3, and thesecond stage was attached on March 4.

The spacecraft arrived at the Cape and was moved into HangarAO on March 1. INSAT was moved into the Explosive SpacecraftAssembly and Encapsulation Building No. 60A on March 17, and thespacecraft is scheduled to be mated with the Payload AssistModule, which has replaced the Delta third stage, on March 26.The INSAP/Payload Assist Module assembly is scheduled to be matedwith the rest of the launch vehicle on the pad on March 30. Thepayload fairing, which protects the spacecraft in Earth'satmosphere, is scheduled to be attached on April 2.

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INSAT-lA SPACECRAFT MISSIONTRAJECTORY MARK EVENTS

EVENT TIME (SEC)Stage 1 Liftoff 0(6) Solid Motors Burnout 56.950(3) Solid Motors Ignition 62.000Jettison (3) Solid Motor Casings 70.000Jettison (3) Solid Motor Casings 71.000(3) Solid Motors Burnout 119.150Jettison (3) Solid Motor Casings 125.500Main Engine Cutoff 223.824Vernier Engine Cutoff 229.824Stage I-1I Separation 231.824Jettison Fairing 241.00CSecond Engine Cut Off Command 547.336Final Cutoff--Stage II 547.741Start Stage III Ignition Time Delay Relay 1125.555Fire Spin Rockets 1125.555Jettison Stage II 1127.555Stage III Ignition 1165.555Stage III Burnout 1251.925Jettison Stage III* 2451.925*First Apogee 20181.853

*To be ground command approximately 20 minutes after TECO

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NASA/INSAT TEAM

NASA HeadquartersDr. Stanley I. Weiss Associate Administrator for

Space Transportation OperationJoseph B. Mahon Director, Expendable Launch

VehiclesPeter Eaton Program Manager, DeltaR. E. Smylie Associate Administrator for

Space Tracking and Data Systems

Goddard Space Flight CenterWilliam C. Keathley Director, Project ManagementDavid W. Grimes Delta Project ManagerWilliam R. Russell Deputy L3lta Project Manager,

TechnicalJohn D. Kraft Manager, Delta Mission Analysisand IntegrationPhilip B. Frustace INSAT Mission Integration

ManagerRobert I. Seiders Mission Operations and Network

Support ManagerRay Mazur Mission Support

Kennedy Space CenterRichard G. Smith DirectorThomas S. Walton Director, Cargo OperationsCnarles D. Gay Director, Expendable Vehicles

OperationsD. C. Sheppard Chief, Automated Payloads

Division

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Kennedy Space Center (continued)Wayne L. McCall Chief, Delta Operations

Division

David Bragdon Spacecraft Coordinator

Department of Space, Government of India (INSAT-1 Space SegmentProject)Professor S. Dhawan Chairman, Space CommissionProfessor U. R. Rao Chairman, INSAT-1

Space Segment Project BoardMr. P. P. Kale Project Director, INSAT-1

Space Segment ProjectProfessor J. P. Singh Program Director, INSAT

Program OfficeDr. S. Vasantha Deputy Project Director,INSAT-1 Space Segment Project

ContractorsFord Aerospace and SpacecraftCommunications Corp.Western DevelopmentLaboratories DivisionPalo Alto, Calif.McDonnell Douglas Delta Launch Vehicle and PAM-DAstronautics Company Payload StageHuntington Beach, Calif.Rocketdyne Division First Stage Engine (RS-27)Rockwell InternationalCanoga Park, Calif.Thiokol Corp. Castor IV Strap-on Solid FuelHuntsville, Ala. MotorsTRW TR-201 Second Stage EngineRedondo Beach, Calif.Delco Guidance CcmputerSanta Barbara, Calif.

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Indian National Satellite System-1 Press Kit