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GSAT-3

GSAT-3, also known as EDUSAT, is an Indian geostationary communications satellite developed and launched by the Indian Space Research Organisation (ISRO) on 20 September 2004 aboard the GSLV-F01 rocket from Sriharikota, marking the first satellite built exclusively for the educational sector to support distance learning from school to higher education levels across remote areas of India. Built on the I-2000 satellite bus platform, it has a launch mass of 1,950.5 kg, dimensions of 2.54 m × 1.525 m, and generates 2,040 W of power, with a planned minimum mission life of seven years. The satellite carries 12 transponders, including five Ku-band transponders for spot beams covering specific regions of India, one Ku-band transponder for national coverage, and six extended C-band transponders providing all-India footprint for broadcast services. Positioned in geostationary orbit at 74° East longitude alongside METSAT (KALPANA-1) and INSAT-3C, it was initially placed into a geosynchronous transfer orbit with a perigee of 180 km and apogee of 35,985 km before being raised to its operational slot using its onboard Liquid Apogee Motor. EDUSAT's primary objective was to enhance educational outreach through interactive multimedia and teleconferencing, enabling virtual classrooms and resource sharing to bridge the digital divide in underserved regions. The satellite operated for six years until it was decommissioned in September 2010 due to power degradation and relocated to a graveyard orbit, where it remains inactive as of 2025.

Background

Development

The development of GSAT-3, also known as EDUSAT, was initiated under the Indian National Satellite (INSAT) system in the early 2000s as part of the Indian Space Research Organisation's (ISRO) efforts to leverage for socio-economic development, particularly to bridge educational gaps in remote and underserved regions of . This initiative stemmed from the recognized need for a dedicated platform to support distance learning, tele-education, and telemedicine amid growing demands for accessible education beyond urban centers. In October 2002, formally conceived the EDUSAT project following consultations that highlighted the limitations of existing communication satellites in meeting specialized educational broadcasting requirements..pdf) The project received approval from the later that year, marking a significant step in 's expansion of the INSAT constellation to include thematic satellites tailored for public service applications. Development proceeded rapidly under the oversight of the , with funding allocated through annual budgetary provisions to support 's satellite programs. Key to the project's success was extensive collaboration with educational stakeholders, including the (IGNOU) for content curation and program design, as well as multiple state governments to identify regional needs and ensure localized implementation of networks. coordinated requirements gathering through workshops and pilot studies involving these partners, focusing on interactive multi-point connectivity for classrooms and training centers across diverse geographies. This partnership model emphasized 's role in providing the technical backbone while educational entities handled curriculum and utilization strategies. The satellite was constructed at ISRO's U. R. Rao Satellite Centre (URSC) in Bengaluru, which served as the lead facility for design, assembly, and testing. Drawing on the proven I-2K bus platform—ISRO's standard 2,000 kg-class geostationary satellite architecture—the team integrated the payload and subsystems over approximately two years. Assembly and integration were finalized in the months leading up to launch, enabling the satellite to meet stringent performance criteria for educational broadcasting within the compressed timeline..pdf)

Objectives

GSAT-3, also known as EDUSAT, was designed to provide interactive education services ranging from school-level to , targeting remote and underserved regions across to facilitate distance learning where traditional infrastructure is limited. The satellite aimed to deliver high-quality educational content through audio-visual mediums, enabling between educators and students in areas lacking adequate schooling facilities. A core objective was to support two-way video conferencing, digital classrooms, and broadband-like connectivity for educational purposes, with the capacity to connect over 5,000 remote terminals in its operational phases, thereby linking thousands of institutions nationwide. This included provisions for on-demand video programming and virtual learning environments to enhance teacher training and curriculum delivery in isolated locations. The mission integrated with ground infrastructure comprising satellite interactive terminals (SITs) for and receive-only terminals (ROTs) for broadcast reception, supported by and regional hubs to form the EDUSAT network managed under ISRO's oversight. These elements enabled a scalable system for educational and . The long-term goal was to bridge the by prioritizing underserved states such as , , and the northeastern region, where initial implementations connected schools and training centers to central content providers. To achieve regional targeting, the satellite utilized Ku-band spot beams focused on high-need areas.

Design

Spacecraft bus

GSAT-3 utilizes ISRO's I-2K , a standardized and modular platform developed for geostationary communication satellites to support reliable operations in orbit. This bus provides the foundational architecture, enabling efficient integration of subsystems while accommodating the demands of extended missions in the harsh . The core structure of the I-2K bus is a cylindrical frame constructed from aluminum alloy, specifically AA 7075 for the panels and AA 2014 for the end rings, offering high strength-to-weight ratio suitable for launch stresses and orbital stability. Measuring 2.54 meters in height and 1.525 meters in diameter, this open design facilitates the mounting of internal components and protects against structural loads during ascent and deployment. Deployment mechanisms are integral to the bus, allowing for the extension of antennas and solar arrays post-launch to achieve full operational configuration in . These systems ensure precise positioning and unfurling, minimizing risks associated with vibration and . Thermal control is managed through a combination of passive elements, such as blankets, and active components like electrical heaters, to regulate temperatures across the in the vacuum and radiative conditions of geostationary space. This approach maintains component integrity by countering extreme diurnal variations and solar exposure. The onboard computer subsystem, part of the command and data handling architecture, processes telecommands from ground stations, manages telemetry data, and oversees attitude control and housekeeping functions for autonomous operation.

Payload

The payload of GSAT-3, also known as EDUSAT, consists of multiple transponders designed primarily for educational broadcasting, enabling interactive across . It includes six upper extended C-band transponders, each providing a 36 MHz for national coverage, supporting broad-area of educational with an effective isotropic radiated (EIRP) of 36 dBW at the edge of coverage. In the Ku-band, the payload features five lower Ku-band transponders configured for spot beams targeting specific regions such as North, , and , each with 36 MHz and 55 dBW EIRP at the edge of coverage to enhance signal strength in focused areas. Complementing these is one lower Ku-band national beam transponder, also with 36 MHz and 48 dBW EIRP, for wider continental coverage. The antenna subsystem supports these transponders through deployable reflectors: a 2.0 m shaped reflector for the C-band national beam to achieve uniform coverage, and a 1.2 m multiple spot beam reflector for the Ku-band to precisely direct signals to regional targets. These configurations ensure efficient beam shaping and minimal interference, optimizing the satellite's role in educational .

Specifications

Mass and dimensions

GSAT-3 had a launch mass of 1,950.5 kg and a dry mass of 819 kg. The satellite carried approximately 1,131 kg of , consisting of MON-3 oxidizer and MMH , primarily for orbit raising maneuvers using its 440 N liquid apogee motor. In its stowed configuration, the overall dimensions measured 2.54 m × 1.525 m. Upon deployment in orbit, the arrays spanned approximately 10.9 m to generate the required power.

Power and propulsion

The power subsystem of GSAT-3, built on ISRO's I-2K , relies on four solar panels, each measuring 2.54 m by 1.525 m, to generate 2,040 of electrical at the end of life (EOL). These panels, equipped with high-efficiency multi-junction solar cells, provide the primary energy source for the satellite's operations throughout its designed 7-year mission life, during which gradual degradation in panel efficiency is expected due to and thermal cycling. For periods of when solar input is unavailable, the system incorporates two 24 Ah nickel-cadmium (Ni-Cd) batteries to ensure uninterrupted to critical subsystems. Power is distributed via a regulated 28 V DC bus, which supplies the payload transponders, attitude control systems, and other onboard electronics, maintaining stable voltage levels to support reliable performance. The propulsion subsystem employs a bipropellant using MON-3 as the oxidizer and (MMH) as the fuel. At its core is a 440 N liquid apogee motor (LAM) mounted on the anti-earth (AEV) face, primarily utilized for orbit raising from the initial geosynchronous transfer (GTO) to the final geostationary (GEO). For fine orbit adjustments, station-keeping, and three-axis stabilization, the satellite features eight 22 N thrusters and eight 10 N reaction thrusters, integrated with momentum wheels, magnetic torquers, and sensors to maintain precise pointing accuracy.

Launch

Vehicle and site

GSAT-3 was deployed using the (GSLV Mk.I) in its F01 configuration, a multi-stage developed by the Space Research Organisation (). This vehicle featured four liquid-propellant strap-on boosters attached to a solid-propellant core first stage, a liquid-propellant second stage powered by the Vikas engine, and a cryogenic upper stage sourced from . The GSLV Mk.I stood approximately 49 meters tall with a lift-off mass of 414 tonnes and was capable of delivering up to 2,000 kg of payload to geosynchronous transfer orbit (GTO). For the GSAT-3 mission, the 1,950 kg satellite was accommodated within these parameters, marking the first operational flight of the GSLV series and advancing India's capability for independent heavy-lift launches. The launch occurred from the First Launch Pad (FLP) at the Satish Dhawan Space Centre (SDSC) SHAR, located in Sriharikota, Andhra Pradesh, India, approximately 80 km north of Chennai on the Bay of Bengal coast. Pre-launch preparations included the satellite's assembly and testing at ISRO's facilities in Bengaluru before transportation to SDSC SHAR for integration with the GSLV Mk.I vehicle, encompassing payload fairing enclosure, fueling, and system checks to ensure compatibility and mission readiness.

Sequence

The GSLV Mk.I F01, carrying the GSAT-3 satellite, lifted off from the on 20 September 2004 at 10:31:00 UTC (16:01 IST). The launch vehicle, configured with a solid-propellant first stage core augmented by four liquid strap-on boosters, followed a nominal ascent profile into a geosynchronous transfer orbit. The flight sequence commenced with ignition of the strap-on boosters 4.8 seconds prior to liftoff, followed immediately by the first stage core ignition at T+0. The first stage core burned out at T+104 seconds, while the strap-on boosters continued until T+150 seconds, after which the second stage ignited at the same instant to maintain acceleration. The was jettisoned at T+227 seconds when the vehicle reached an altitude of approximately 115 km. The second stage burned for about 138 seconds, shutting down at T+288 seconds. The cryogenic third stage ignited shortly thereafter at T+304 seconds, providing the upper stage velocity increment over a burn duration of roughly 695 seconds. The third stage shut down at T+999 seconds, achieving a velocity of 10.2 km/s. GSAT-3 separated from the at T+1,014 seconds, approximately 5,000 km downrange from the launch site, and was injected into a with a perigee altitude of 180 km, apogee of 35,985 km, inclination of 19.2 degrees, and of 10.5 hours. Post-separation, ground stations conducted initial health checks on the satellite, confirming nominal performance of its systems prior to the start of orbital maneuvers.

Deployment and operations

Orbital maneuvers

Following separation from the on September 20, 2004, GSAT-3 (EDUSAT) was injected into a with a perigee altitude of 181 km, an apogee altitude of 36,000 km, and an of 19.3°. The satellite then performed three apogee-raising maneuvers using its onboard 440 N liquid apogee motor (LAM), fueled by and , to circularize the orbit and reach at 74° East . The first apogee-raising burn was executed on September 21, 2004, firing the for 2,996 seconds and raising the perigee to 8,800 km while maintaining the apogee at 36,000 km and reducing the inclination to 7.15°. Subsequent burns, conducted in stages over the following days, progressively raised the perigee further, reduced the inclination, and enabled drift to the operational longitude to achieve the final circular . The propulsion system referenced here is the I-2K satellite bus's bipropellant setup, detailed in the specifications section. Soon after injection into , the satellite's two solar arrays were automatically deployed, with telemetry confirming normal deployment and overall satellite health. The east and west reflectors, part of the multi-beam antenna system, were also deployed during the transfer phase to prepare for operational configuration. Initial yaw maneuvers, supported by reaction control thrusters and momentum wheels, established three-axis stabilization for the insertion. The final orbit was a circular at an altitude of 35,786 km with an inclination of less than 0.1°, enabling co-location with INSAT-3C and at 74° East.

Mission phases

Following its launch on 20 September 2004, GSAT-3 underwent a commissioning phase that included orbit-raising operations using its onboard Liquid Apogee Motor and comprehensive activation tests to verify functionality and subsystem performance. The satellite was successfully positioned in at 74° East longitude and entered operational service on 24 September 2004. During nominal operations, GSAT-3 maintained its geostationary position through daily station-keeping maneuvers executed with 22 N bipropellant thrusters, alongside power management starting in 2005 to ensure stable attitude control and orbit stability. The satellite operated in co-location with INSAT-3C and METSAT-1 (also known as ) at 74° East, facilitating coordinated orbital slot usage without interference.

Applications

Educational services

GSAT-3, operating as EDUSAT, facilitated connectivity for virtual classrooms across approximately 56,000 schools and colleges in through VSAT networks, enabling interactive primarily in underserved rural regions. This infrastructure supported the delivery of live educational content from central hubs to remote receive-only terminals (ROTs) and satellite interactive terminals (SITs), allowing real-time teacher-student interactions without reliance on terrestrial infrastructure. The satellite's educational services were bolstered by partnerships with the National Council of Educational Research and Training (NCERT), its Central Institute of Educational Technology (CIET), and various state education departments, which coordinated curriculum broadcasting and program development. These collaborations enabled the transmission of standardized educational materials aligned with national syllabi, focusing on subjects like , , and vocational training to bridge urban-rural disparities. Interactive sessions were enabled via five Ku-band spot beams targeting regional hubs, including those in (northern), (eastern), and (southern), alongside coverage for northeastern and western areas, supporting two-way audio-video communication. Complementing this, dedicated programs for teachers utilized the satellite's tools, such as teleconferencing modules, to build capacity in handling content and interactive teaching methods, thereby enhancing pedagogical skills in remote institutions. EDUSAT's services significantly improved access to quality and contributed to higher engagement in distance learning initiatives across the country.

VICTERS channel

VICTERS, an acronym for Versatile Enabled Resource for Students, represents Kerala's pioneering initiative utilizing the GSAT-3 (EDUSAT) satellite. Inaugurated on 28 July 2005 by then-President in , with formal channel launch on 3 August 2006, it leverages the satellite's communication payloads to deliver targeted educational content to rural and remote schools across the state. This network marked India's first dedicated broadband setup on EDUSAT for school-level , emphasizing classrooms with two-way to bridge urban-rural divides. The channel broadcasts a range of programs tailored for students in grades 1 through 12, alongside teacher training modules and cultural programming, all aligned with the state curriculum to supplement classroom learning. Uplink operations originate from the dedicated studio and transmission facility in Poojapura, , with statewide reception enabled through the satellite's extended C-band transponders for reliable coverage in underserved areas. Notable offerings include interactive quizzes like Haritha Vidyalayam for environmental awareness, hands-on experiments demonstrating practical concepts, and language lessons via engaging storytelling in series such as E3. These programs foster conceptual understanding and skill development, with early emphasis on real-time interaction via satellite-linked terminals in schools. By 2010, VICTERS had significantly expanded its reach, incorporating live streaming while maintaining delivery, and became deeply integrated into Kerala's curricula through initiatives like First Bell classes. The platform served over 5 million students and 200,000 teachers, contributing to widespread adoption in daily educational routines and enhancing access to quality resources during the GSAT-3 operational phase. Following GSAT-3's decommissioning in the mid-2010s, VICTERS continued operations using subsequent satellites such as GSAT-18.

End of mission

Decommissioning

GSAT-3, also known as EDUSAT, was officially decommissioned on 30 September 2010 after approximately six years of operation, primarily due to on-board power constraints that limited its capacity and led to a premature end of its designed seven-year lifespan. These power issues necessitated the gradual shifting of its 30 educational networks to INSAT-4CR starting in September 2008, with the remaining networks idled following deactivation. As part of the end-of-life procedures, the satellite was maneuvered using its remaining to a supersynchronous above the geostationary belt. To maintain continuity in educational services, traffic from GSAT-3 was migrated to a combination of existing and subsequent satellites, including INSAT-4CR, GSAT-12, GSAT-18, INSAT-3A, and INSAT-3C, which supported ongoing tele-education and related applications. This transition highlighted planning gaps in dedicated educational satellite replacements, with future missions like GSAT-14 proposed in the 12th to address such needs. The decommissioning process adhered to international orbital debris mitigation guidelines, such as those from the Inter-Agency Coordination (IADC), by elevating the satellite to a supersynchronous disposal to minimize collision risks in the geostationary region.

Legacy

GSAT-3, also known as EDUSAT, pioneered satellite-based as the nation's first dedicated for the educational sector, enabling interactive distance learning across remote and underserved regions. Launched in 2004, it provided multi-channel video and audio transmission capabilities, connecting thousands of schools, colleges, and centers, and established a model for leveraging to bridge educational disparities. It connected approximately 56,000 schools and colleges across 26 states and 3 union territories, benefiting around 15 million students annually by December 2012. This initiative influenced subsequent missions by demonstrating the viability of geostationary satellites for targeted societal applications, including later communication satellites that expanded educational and developmental outreach. The mission's educational outcomes significantly enhanced and in remote areas, with studies indicating substantial improvements in student engagement and utilization. For instance, research revealed significant increases in student attendance and learning gains, alongside positive shifts in attitudes toward among participants in EDUSAT-enabled classrooms. These impacts were particularly notable in states like and , where thousands of primary and secondary schools were linked, fostering uniform teaching standards and greater involvement in educational programs. Technologically, GSAT-3 validated the I-2K platform, a 2,000 kg-class geostationary system developed by , which provided reliable power, propulsion, and payload accommodation for its 12 transponders. This successful deployment confirmed the bus's robustness for extended missions, serving as a foundational design for future series satellites, including GSAT-4, GSAT-6, and GSAT-10, thereby advancing India's indigenous satellite manufacturing capabilities. Following the exhaustion of its operational life in due to power degradation, GSAT-3 was decommissioned and raised to a above the geostationary belt in accordance with international mitigation guidelines. It continues to be tracked by global space surveillance networks under catalog number 28417, ensuring safe disposal without posing risks to active .

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