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INSAT-1A

INSAT-1A was the first multipurpose satellite in India's Indian National Satellite (INSAT) system, launched on 10 April 1982 from Cape Canaveral, Florida, aboard a Delta 3910 PAM-D rocket by the United States.^[1] Designed and built by Ford Aerospace & Communications Corporation to meet India's specific requirements for domestic communications and meteorological services, it operated in geostationary orbit at 74° East longitude with a launch mass of 1,152 kg, a power output of approximately 1,185 W from deployable solar arrays, and a designed mission life of 7 years.^[1] The satellite's primary payloads included 12 C-band transponders for fixed satellite services in telecommunications, three S-band transponders (two operational plus one backup) for direct television broadcasting to community sets, and a Very High Resolution Radiometer (VHRR) for cloud motion vector derivation and meteorological imaging in visible and infrared bands.^[2] It also supported data collection platforms and search and rescue operations, marking India's entry into operational space-based services for national development.^[3] Despite its innovative design featuring three-axis stabilization and a momentum-biased attitude control system, INSAT-1A encountered significant challenges shortly after launch.^[1] A partial failure in the deployment of one solar array reduced power availability, and subsequent software glitches and excessive propellant consumption for attitude control led to the satellite's abandonment on 6 September 1983, after only about 16 months of partial operations.^[4] During its active period, it successfully demonstrated key capabilities, including the operational use of the Master Control Facility in Hassan, Karnataka, and the Indian Space Network for ground support, paving the way for subsequent INSAT satellites like INSAT-1B, which replaced it at the same orbital slot.^[2] The mission highlighted early lessons in satellite reliability and international collaboration, as INSAT-1A was India's first geostationary operational satellite procured from abroad.^[1]

Background

INSAT Program

The Indian National Satellite (INSAT) system was approved in 1977 as a cooperative venture between the Indian Space Research Organisation (ISRO) and the Department of Space (DoS), marking India's shift toward an integrated operational satellite network with involvement from international entities like the International Telecommunication Satellite Organization (INTELSAT) for capacity leasing and technical coordination.^[5]^[6] This initiative built on the foundational experiences from prior experimental missions, evolving from the scientific focus of Aryabhata—launched in 1975 to study X-ray emissions and aeronomy—to the remote sensing capabilities of Bhaskara in 1979, which tested microwave and infrared imaging for resource mapping.^[7] The transition emphasized geostationary orbits to ensure wide-area coverage over India's diverse terrain, addressing limitations of low-Earth orbit satellites in providing continuous service. The core objectives of the INSAT program centered on establishing a unified geostationary platform that combined telecommunications, television broadcasting, and meteorological data relay to bridge urban-rural divides and enhance national resilience. Specifically, it aimed to support telephony expansion in remote areas, nationwide TV distribution for education and information dissemination, and real-time weather monitoring for cyclone warnings and agricultural planning, thereby contributing to disaster management and socioeconomic development.^[8] These goals reflected India's strategic prioritization of space applications for public welfare, with the system designed to handle multiple transponders for simultaneous services without relying on fragmented international leases. Key international collaborations underpinned the program's early phases, with Ford Aerospace & Communications Corporation of the USA contracted to design and build the first-generation INSAT satellites under a technology transfer agreement that enabled ISRO engineers to acquire hands-on expertise in satellite assembly and testing.^[9] NASA facilitated launch services for the inaugural INSAT-1A using a Delta 3910 rocket from Cape Canaveral, ensuring reliable deployment while adhering to technology safeguards.^[10] INSAT-1A became the series' first satellite, operationalized in 1982 to demonstrate the multipurpose framework.^[7]

Mission Objectives

The primary objectives of INSAT-1A were to establish a nationwide telecommunications relay system using 12 C-band transponders for fixed satellite services, facilitate television broadcasting to remote areas via two high-power S-band transponders, and collect meteorological data for weather forecasting through a Very High Resolution Radiometer (VHRR) capable of providing visible and infrared imagery.^[2]^[1] These capabilities aimed to enhance connectivity and information dissemination across India's diverse geography, supporting both urban and rural populations by enabling reliable voice, data, and video transmission.^[11] Secondary goals included supporting search and rescue operations through dedicated transponders that could receive and relay distress signals from ships, aircraft, and individuals in distress, as well as enabling data collection from unattended remote platforms such as hydrological and oceanographic sensors via a data relay transponder.^[3]^[2] These features were designed to bolster disaster management and environmental monitoring, providing real-time alerts and data to ground stations for timely response.^[11] INSAT-1A was positioned in geostationary orbit at 74° East longitude to deliver fixed satellite services over India, including remote areas and offshore islands, as well as neighboring regions for extended coverage.^[2]^[3] The planned mission duration was seven years, emphasizing high reliability for continuous, uninterrupted service to meet long-term national infrastructure needs.^[1]

Design and Specifications

Spacecraft Bus

The INSAT-1A spacecraft utilized a custom box-shaped bus developed by Ford Aerospace, featuring approximate dimensions of 2.0 m in height by 1.5 m in width and depth, designed for three-axis stabilization with a momentum-biased attitude control system to accommodate antenna pointing requirements.^[12]^[1] The satellite had a launch mass of 1,152 kg, including propellants and payloads, and a dry mass of 650 kg once on station.^[1]^[13] The power subsystem relied on a deployable solar array consisting of five panels oriented along a single axis toward the sun, capable of generating up to 1,185 W at the beginning of life to support all bus and payload operations.^[14] Two 12 Ah nickel-cadmium (Ni-Cd) batteries, each comprising 28 series-connected cells, provided backup power during eclipse periods when solar input was unavailable, ensuring continuous subsystem functionality.^[15] Propulsion was provided by a bipropellant system using nitrogen tetroxide as oxidizer and monomethylhydrazine as fuel, with the primary R-4D-11 apogee motor handling orbit insertion and axial thrusters for station-keeping maneuvers.^[16]^[1] Attitude control provided three-axis stabilization using a momentum wheel, supplemented by hydrazine thrusters for fine adjustments and a despun platform that allowed precise orientation for payload integration.^[17] Thermal control and attitude subsystems included earth sensors, sun sensors, and thrusters for fine adjustments during operational phases.^[17]^[12]

Payloads

INSAT-1A featured a suite of payloads designed for multi-purpose geostationary operations, encompassing telecommunications, broadcasting, and meteorological observation to support India's national communication and weather monitoring needs. The primary payloads included communication transponders in C- and S-bands for telephony, data relay, and television distribution, alongside meteorological instruments for cloud motion vector derivation and environmental data collection. These payloads were integrated to provide coverage over the Indian subcontinent and adjacent regions, with a total power allocation of approximately 300 W from the spacecraft bus.^[18] The communication subsystem comprised 12 C-band transponders operating with an uplink frequency of 5.935-6.425 GHz and downlink of 3.700-4.200 GHz, each offering a bandwidth of 36 MHz for fixed satellite services such as telephony and data relay. These transponders, each powered by a 4.5 W traveling wave tube amplifier (TWTA), delivered an effective isotropic radiated power (EIRP) of at least 32 dBW over the primary coverage area, enabling support for up to 4,375 two-way voice circuits nationwide. Additionally, three S-band transponders were included: two high-power units at 20 W each for direct TV broadcasting to community receivers, and one lower-power unit at 2.5 W for telecommunications, operating around 2.5 GHz to facilitate high-fidelity audio and video distribution to remote areas.^[18]^[19]^[15] Meteorological capabilities were provided by the Very High Resolution Radiometer (VHRR), a two-channel imager for Earth disc observation in visible and thermal infrared spectra. The visible channel operated in the 0.55-0.75 μm wavelength range with a spatial resolution of 2.75 km at nadir, suitable for cloud top imaging and motion vector analysis, while the thermal infrared channel covered 10.5-12.5 μm with 11 km resolution for sea surface temperature and cloud pattern monitoring. Complementing the VHRR, the Data Collection Service (DCS) enabled relay of environmental data from ground-based platforms, using a UHF uplink in the 402.65-402.85 MHz band (G/T of -19 dB/K) and C-band downlink with an EIRP of up to 21 dBW, supporting applications like hydrological and meteorological data gathering from remote sensors.^[20]^[21]^[18] Antenna systems supporting these payloads included approximately 1.4 m diameter dual-gridded parabolic reflectors for C-band operations, providing a global beam with expanded coverage from the Middle East to Southeast Asia and an EIRP edge of 39 dBW over India. S-band communications utilized horn feeds for spot beam coverage focused on the Indian subcontinent, while the VHRR employed a dedicated scan mirror mechanism for full-disc (20° × 20°) or sector scans over the region. Overall, the payloads were engineered for simultaneous operation, with the bus providing pointing accuracy and power distribution to ensure reliable service delivery.^[22]^[1]

Launch

Preparation and Launch Vehicle

The development of INSAT-1A began in 1978 when the Indian Space Research Organisation (ISRO) awarded a contract to Ford Aerospace & Communications Corporation in the United States to design and build the satellite, marking the start of the INSAT-1 series under a collaborative effort to establish India's multi-purpose geostationary satellite system.^[15] The satellite underwent extensive testing at Ford Aerospace facilities to verify its structural integrity, thermal performance, and subsystem functionality prior to shipment.^[23] Following completion of these ground tests, INSAT-1A was shipped to the United States in late 1981 for final preparations and integration with the launch vehicle.^[23] Under a bilateral agreement between India and the United States, formalized through a Memorandum of Understanding signed on July 18, 1978, and a subsequent Launch Services Agreement on November 18, 1980, NASA agreed to provide launch services on a reimbursable basis at a fixed price of $25 million.^[23] This arrangement facilitated the use of the Delta 3910/PAM-D launch vehicle, specifically configured for INSAT-1A's deployment into a geosynchronous transfer orbit targeting eventual positioning in geostationary orbit at 74° East longitude. The Delta 3910 consisted of an Extended Long Tank Thor booster as the first stage, nine Castor IV solid-propellant strap-on motors for augmented thrust, a TR-201 liquid-propellant second stage, and the Payload Assist Module-D (PAM-D) perigee kick motor for final orbit insertion.^[23] Compatibility checks confirmed that the satellite's dimensions fit within the vehicle's 8-foot (2.44 m) diameter fairing, ensuring secure encapsulation during ascent.^[23] Pre-launch activities took place at Cape Canaveral's Launch Complex 17A, where the satellite arrived for integration with the Delta stack in early 1982 under the oversight of a joint ISRO-NASA operations team.^[23] This included final electrical and mechanical interfacing, propulsion system verifications, and environmental simulations to mitigate risks. To cover potential failures, INSAT-1A was insured for up to six months (approximately 180 days) post-launch by a consortium led by New India Assurance, providing financial protection valued at around Rs 341.50 crore at the time.^[24] These preparations culminated in the vehicle's rollout to the pad, setting the stage for the April 10, 1982, liftoff.

Launch Sequence

The launch of INSAT-1A took place on 10 April 1982 at 06:47 UTC from Cape Canaveral's Space Launch Complex 17A, utilizing a Delta 3910 launch vehicle augmented with a Payload Assist Module-D (PAM-D) upper stage. At liftoff (T+0), six of the nine Castor IV solid-propellant strap-on boosters ignited simultaneously with the liquid-fueled Thor core stage, providing initial ascent thrust. The remaining three strap-ons ignited at T+62 seconds, with the first set burning out at approximately T+57 seconds and the second set at T+119 seconds; jettison of the spent casings occurred progressively between T+70 and T+126 seconds.^[23] The Thor core stage continued propulsion until main engine cutoff (MECO) at T+224 seconds, after which stage separation from the second stage occurred at T+232 seconds. The restartable Aerojet AJ10-118K second stage then ignited at T+274 seconds, burning for about 432 seconds to reach cutoff (SECO) at T+548 seconds and establish a low parking orbit. Following a coast phase of roughly 10 minutes, the PAM-D and satellite stack separated from the second stage at T+1,128 seconds. The PAM-D Star 48B solid motor ignited shortly thereafter at T+1,166 seconds, firing for 87 seconds until burnout at T+1,252 seconds, injecting the payload into a geosynchronous transfer orbit (GTO) with a perigee altitude of approximately 167 km, an apogee of 35,800 km, and an inclination of 28.4 degrees.^[23] The INSAT-1A spacecraft separated from the expended PAM-D stage via ground command approximately 20 minutes after PAM-D burnout, at T+2,452 seconds, marking the end of the launch vehicle's role. Immediately following separation, the satellite acquired a Sun-pointing attitude using its three-axis control system and onboard hydrazine thrusters for initial stabilization and orientation for the apogee kick motor firing. The transfer orbit parameters provided the necessary high apogee for subsequent maneuvers. About 5.6 hours post-launch, at the first GTO apogee (T+20,182 seconds), the satellite's apogee kick motor (AKM) fired to raise perigee altitude, achieving circular geostationary orbit (GEO) at 35,786 km over the equator. Final station-keeping maneuvers positioned INSAT-1A at 74° East longitude.^[23]

Operations

Commissioning Phase

Following its launch on April 10, 1982, INSAT-1A was rapidly acquired by Indian ground stations, including the Master Control Facility (MCF) in Hassan, Karnataka, which tracked the satellite within minutes of its injection into geosynchronous transfer orbit (GTO), supported by Telemetry, Tracking, and Command (TTC) stations in Ahmedabad and Bangalore for initial signal reception and monitoring.^[23]^[12] Telemetry verification commenced immediately after separation from the Delta 3910 launch vehicle, confirming nominal spacecraft health parameters such as thermal status and subsystem responsiveness during the transfer orbit phase.^[23] Key commissioning activities in April focused on orbit raising and stabilization. The initial post-separation spin rate of approximately 40 rpm was established for attitude stability, with subsequent adjustments using the bipropellant thrusters to maintain nutation damping and prepare for major maneuvers.^[23] Partial deployment of the solar array was achieved shortly after launch, extending to about 50% of its full span due to a jamming issue with one panel, which limited power generation and led to stabilization of the power subsystem at roughly 600 W—half the nominal 1,185 W capacity—supplemented by NiCd batteries during eclipses and low-output periods.^[12]^[1] Orbit circularization began with the firing of the Apogee Kick Motor (AKM) approximately 5.5 hours after launch at the first apogee, raising the perigee to geosynchronous altitude; additional thruster firings on April 11 and 12 using the liquid apogee motor (LAM) refined the orbit to 35,031 km × 35,781 km at an inclination of 0.5°, targeting 74° East longitude.^[23]^[12] Attitude control was verified through activation of the three-axis stabilization system, incorporating two momentum wheels and a reaction wheel for Sun-pointing during transfer, transitioning to geostationary drift orbit by late April.^[23] Into May, further system checks confirmed the functionality of the communication payloads, with basic activation of the 12 C-band and 3 S-band transponders for signal testing after the C-band antenna deployment on April 22, despite initial delays from deployment anomalies.^[12] The meteorological payload, including the Very High Resolution Radiometer (VHRR), was tested, yielding the first Earth image in late April 1982, marking the initial verification of cloud motion and thermal infrared imaging capabilities over the Indian subcontinent.^[25] By early May, the satellite reached its operational slot at 73.5° East, completing the core commissioning sequence ahead of full payload handoff to user agencies.^[12]

In-Orbit Performance

INSAT-1A provided operational services from its activation in late April 1982 until attitude control propellant depletion, exacerbated by power limitations and software issues, led to its deactivation on 6 September 1982, delivering approximately five months of effective functionality despite design expectations for a seven-year lifespan.^[1] During this time, the satellite's telecommunications payload was successfully commissioned, enabling initial national coverage for voice and data communications through its C-band transponders.^[26] The C-band transponders supported two-way long-distance telephone circuits, contributing to the expansion of India's telecommunication infrastructure by providing connectivity across the country.^[27] Additionally, the S-band transponders facilitated direct television broadcasting, allowing Doordarshan to reach a wider audience with programs.^[28] By mid-1982, the satellite had demonstrated its capacity for supporting thousands of voice circuits equivalent, though full utilization was limited by the impending power constraints.^[29] In the meteorological domain, INSAT-1A's Very High Resolution Radiometer (VHRR) generated full-disk and sector images for deriving cloud motion vectors, aiding in weather monitoring and forecasting.^[30] These observations proved valuable for tracking synoptic systems, such as the cyclone that struck Orissa in early June 1982, where VHRR imagery supported timely analysis and early warnings during the monsoon season.^[31] The satellite's Data Collection and Dissemination (DCS) transponder relayed environmental data from over 50 ground-based platforms, including hydrological and meteorological sensors, enhancing real-time data gathering for disaster management and resource monitoring across India.^[32] Station-keeping maneuvers kept INSAT-1A positioned at 74° East longitude in geostationary orbit, utilizing bipropellant thrusters for north-south and east-west adjustments to maintain coverage over the Indian subcontinent.^[1] These operations required approximately 10 m/s of delta-V annually under nominal conditions, though actual consumption was influenced by the satellite's early anomalies. Overall, by the time power issues escalated, the total active communication circuits exceeded initial projections, underscoring INSAT-1A's brief but impactful role in service delivery.^[29]

Failure

Deployment Anomalies

Following its launch on April 10, 1982, INSAT-1A encountered significant challenges with the deployment of its solar array, which only partially extended due to issues including a failure in the latching mechanism.^[33] The array, designed to generate about 1200 W of beginning-of-life power, provided reduced power availability as a result, severely constraining the spacecraft's energy from the outset.^[18] Ground controllers mitigated the issue partially by using thruster firings to heat the array in sunlight, allowing limited further extension, though the root cause remained unidentified.^[33] The satellite's antenna systems also suffered deployment issues, with the C-band reflector delayed by 12 days until around April 22, 1982, owing to a glitch in the pyrotechnic sequencer that prevented timely activation.^[34] This postponement required extensive on-orbit maneuvering, consuming valuable propellant. Additionally, the S-band transponders experienced overheating, which degraded performance for direct television broadcasting and search-and-rescue functions.^[25] The stabilization boom failed to fully extend, resulting in an off-axis spin axis that misoriented key sensors and increased reliance on thrusters for attitude corrections.^[33] Linked to an inoperative mechanical latch on the associated mast with solar sail, this anomaly compounded the spacecraft's early instability without achieving full three-axis stabilization as planned.^[33] These deployment failures led to immediate operational strains, including battery overheating due to the power deficit and selective blackouts of non-essential systems to conserve energy.^[35] While no complete system loss occurred, the degraded efficiency hampered commissioning activities and reduced overall payload functionality from the first days in orbit.^[33]

Propellant Exhaustion and Mission End

Shortly after the initial deployment anomalies, INSAT-1A experienced degradation in its attitude control system, including a fault in a valve that required significantly more frequent thruster firings to maintain orientation and compensate for the effects of the undeployed stabilization boom, which had caused persistent misalignment. This elevated usage of the hydrazine-based propulsion system accelerated propellant consumption far beyond nominal rates.^[12]^[31] The spacecraft had been designed for a nominal operational life of seven years, supported by an onboard hydrazine propellant load sufficient for attitude adjustments and station-keeping maneuvers over that period. However, the unanticipated demands from the attitude control issues led to rapid depletion, exhausting the reserves after approximately five months in orbit. By early September 1982, ground controllers at the Master Control Facility in Hassan confirmed that fuel levels were critically low, rendering further maneuvers impossible and compromising the satellite's ability to maintain its geostationary position.^[2]^[36] On 4 September 1982, the primary attitude sensor was deactivated as propellant exhaustion set in, marking the onset of uncontrolled drift. Two days later, on 6 September 1982, INSAT-1A was officially declared non-operational and abandoned by ISRO, with no deorbit burn executed due to the lack of remaining fuel; the satellite was thus left in an uncontrolled geostationary orbit, where it continued to drift and was tracked into the 2000s.^[12]^[35] A joint investigation conducted by ISRO and Ford Aerospace, the satellite's manufacturer, concluded that the mission's terminal failure resulted from the cumulative impact of the earlier deployment problems, particularly the stabilization boom and solar array issues, which indirectly drove the excessive propellant expenditure; the review explicitly cleared ground operations of any command errors or procedural faults.^[31]^[37]

Legacy

Contributions to Indian Space Capabilities

INSAT-1A played a pivotal role in expanding India's telecommunications infrastructure by providing national coverage through its 12 C-band transponders, which supported over 8,000 two-way long-distance telephone circuits accessible from any part of the country, significantly bridging the urban-rural communication divide.^[23] Additionally, its two high-power S-band transponders enabled direct television broadcasting to community receivers in remote and rural areas, facilitating the first nationwide uplink for educational and developmental programs, including those aimed at rural electrification and awareness initiatives.^[2] This capability marked a substantial leap in connecting underserved regions, allowing for real-time dissemination of information to offshore islands and isolated communities.^[6] In meteorology, INSAT-1A's Very High Resolution Radiometer (VHRR) instrument delivered visible and infrared imagery every 30 minutes, laying the groundwork for India's operational satellite-based weather monitoring system and enhancing disaster response capabilities.^[30] The VHRR data supported early cyclone tracking and prediction efforts during its operational period, contributing to improved warnings for tropical storms in the Bay of Bengal and Arabian Sea, and establishing the INSAT series as a cornerstone for meteorological services in India.^[38] Despite its brief operational lifespan, INSAT-1A demonstrated India's proficiency in managing geostationary Earth orbit (GEO) satellites, providing critical momentum to the national program and prompting the swift launch of INSAT-1B in August 1983 as a direct replacement to maintain service continuity.^[29] The mission, developed through a collaborative effort with Ford Aerospace in the United States, transferred valuable technical knowledge to Indian engineers, fostering indigenous expertise in satellite design, ground control, and operations.^[2] Furthermore, the satellite was insured for approximately $64 million, which mitigated financial risks and allowed resources to be redirected toward subsequent INSAT developments without significant budgetary disruption.^[39]

Lessons Learned

The partial deployment of INSAT-1A's solar array and C-band antenna, which compromised power generation and required excessive thruster firings for attitude maintenance, underscored the critical need for enhanced deployment reliability in future designs.^[40] In response, the INSAT-1B incorporated redundant release mechanisms and refined pyrotechnic initiators for solar arrays and antennas, enabling successful deployment after initial challenges through targeted ground commands.^[41] These modifications, informed by post-failure analysis of jamming risks, extended to improved boom designs and pre-launch simulations, reducing the likelihood of mechanical interference in the INSAT series.^[42] INSAT-1A's power subsystem suffered from halved output due to the undeployed solar array, leading to battery overheating and eventual system strain that exacerbated propellant use.^[12] This experience drove the adoption of more robust nickel-cadmium battery configurations with enhanced thermal management in INSAT-1B and later models, alongside the implementation of partial power modes to prioritize essential payloads during anomalies.^[43] Such advancements also influenced greater bus redundancy across the INSAT series, allowing continued operations even if one power channel failed, as demonstrated in INSAT-1C's partial transponder loss without total mission abandonment.^[15] The rapid exhaustion of INSAT-1A's hydrazine propellant—depleted in under five months due to uncontrolled thruster activations from sensor confusion and valve faults—highlighted vulnerabilities in momentum-biased three-axis stabilization under deployment-compromised conditions.^[42] Lessons from this prompted refinements in attitude control for subsequent satellites, including redesigned software to detect and isolate faulty sensor readings from lunar interference, along with automatic telemetry switching to maintain Earth-lock.^[42] The INSAT program shifted toward more propellant-efficient three-axis configurations in later iterations, coupled with advanced ground-based simulations for boom and antenna deployments to minimize in-orbit corrections.^[43] On the programmatic front, INSAT-1A's abrupt failure accelerated the procurement and readiness of backup satellites, with INSAT-1B achieving operational status within about 13 months through expedited testing and integration.^[7] The collaboration with Ford Aerospace revealed gaps in cross-cultural engineering protocols, leading to strengthened international integration processes, including joint failure review committees and clearer subcontractor management guidelines for the INSAT-1 series.^[43] These changes ensured faster anomaly resolution and built resilience into India's geostationary satellite operations.^[15]

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[37]
[PDF] Worldwide Report, Telecommunications Policy, Research ... - DTIC
Oct 26, 1982 · It will study the report to be prepared by Ford Aerospace builders of the satellite who are fully responsible for the mission in the first 180 ...
[38]
[PDF] Cyclone track prediction using INSAT data
Cyclone track prediction uses INSAT data, observing cloud rotation and temperature maps, and extrapolating motion based on past and present locations.
[39]
Isro May Be Paid $65m Insurance For Defunct Satellite
Dec 10, 1997 · Earlier, the consortium led by the New India Insurance had paid ISRO $64 million for the loss of Insat-1A in 1982 and $72 million for the ...
[40]
INSAT-1A
Insufficient relevant content. The provided URL (https://www.isro.gov.in/INSAT_1A.html) contains only the title "INSAT-1A" with no additional details about the satellite's launch date, vehicle, mission, objectives, specifications, outcomes, or notable events.
[41]
https://www.isro.gov.in/INSAT_1B.html
[42]
INSAT 1A: Moonstruck satellite - India Today
Aug 26, 2013 · It was on September 4, the Disaster Day for INSAT as it is ... deployment of the solar sail. Because of the yaw. the sensors were ...
[43]
[PDF] indian space research organisation - ISRO
Designed specifically to meet India's requirements, the INSAT-1 satellites are built by the Ford Aerospace Corporation (FAC) of the United States of America to ...