GSLV (original) (raw)

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GSLV

GSLV
Credit: ISRC

Indian mixed-propulsion orbital launch vehicle for geosynchronous satellites using a LOx/LH2 upper stage developed from Russian technology.

AKA: Geostationary Satellite Launch Vehicle. Status: Active. First Launch: 2001-04-18. Last Launch: 2010-12-25. Number: 6 . Payload: 5,000 kg (11,000 lb). Thrust: 6,810.00 kN (1,530,940 lbf). Gross mass: 402,000 kg (886,000 lb). Height: 49.00 m (160.00 ft). Diameter: 2.80 m (9.10 ft). Apogee: 200 km (120 mi).

The 49 meter tall GSLV was a three stage vehicle. The first stage, GS1, comprised a core motor with 138 metric tons of solid propellant and four strap-on motors each with 40 metric tons of hypergolic liquid propellants (UH25 and N204). The second stage had 39 metric tons of the same hypergolic liquid propellants. The third stage (GS3) was a cryogenic stage with 12.5 metric tons of liquid oxygen and liquid hydrogen.

The aluminum alloy GSLV payload fairing was 3.4 m in diameter and 7.8 m long. GSLV employed a flexible linear shaped charge separation system for the first stage, a pyrotechnically-actuated collet release mechanism for the second stage, and a Merman band bolt cutter separation mechanism for the third stage. Spacecraft separation was by spring thrusters mounted at the separation interface. The three-axis attitude stabilization of GSLV was achieved by autonomous control systems provided in each stage. Single plane engine gimbal controls on the four strap-ons of the first stage were used for pitch, yaw and roll control. The second used engine gimbal control for pitch and yaw and a hot gas reaction control system for roll control. Two swiveling vernier engines using LH2 and LOX provided pitch, yaw and roll control for the third stage during thrust phases. A cold gas orientation system was used during third stage coast phases. The booster's inertial guidance system was located in the equipment bay above the third stage. The closed loop guidance scheme used by the on-board computer ensured the required accuracy in orbital injection conditions.

LEO Payload: 5,000 kg (11,000 lb) to a 200 km orbit at 45.00 degrees. Payload: 2,500 kg (5,500 lb) to a GTO. Development Cost :500.000million.LaunchPrice: 500.000 million. Launch Price :500.000million.LaunchPrice: 45.000 million in 1985 dollars.

Stage Data - GSLV

Stage 0. 4 x GSLV-0. Gross Mass: 45,600 kg (100,500 lb). Empty Mass: 5,600 kg (12,300 lb). Thrust (vac): 735.000 kN (165,234 lbf). Isp: 281 sec. Burn time: 159 sec. Isp(sl): 240 sec. Diameter: 2.10 m (6.80 ft). Span: 2.10 m (6.80 ft). Length: 19.70 m (64.60 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Viking 2. Other designations: Geostationary Satellite Launch Vehicle. Status: Out of Production.
Stage 1. 1 x GSLV-1. Gross Mass: 157,300 kg (346,700 lb). Empty Mass: 28,300 kg (62,300 lb). Thrust (vac): 4,860.070 kN (1,092,587 lbf). Isp: 266 sec. Burn time: 93 sec. Isp(sl): 237 sec. Diameter: 2.80 m (9.10 ft). Span: 2.80 m (9.10 ft). Length: 20.34 m (66.73 ft). Propellants: Solid. No Engines: 1. Engine: PSLV-1. Other designations: Geostationary Satellite Launch Vehicle. Status: In production.
Stage 2. 1 x GSLV-2. Gross Mass: 42,900 kg (94,500 lb). Empty Mass: 5,400 kg (11,900 lb). Thrust (vac): 725.015 kN (162,990 lbf). Isp: 295 sec. Burn time: 149 sec. Isp(sl): 200 sec. Diameter: 2.80 m (9.10 ft). Span: 2.80 m (9.10 ft). Length: 11.60 m (38.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Viking 4. Other designations: Geostationary Satellite Launch Vehicle. Status: In production.
Stage 3. 1 x GSLV-3. Gross Mass: 14,600 kg (32,100 lb). Empty Mass: 2,200 kg (4,800 lb). Thrust (vac): 75.050 kN (16,872 lbf). Isp: 460 sec. Burn time: 675 sec. Diameter: 2.80 m (9.10 ft). Span: 2.80 m (9.10 ft). Length: 8.72 m (28.60 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RD-56M. Other designations: Geostationary Satellite Launch Vehicle. Status: In production.

More at: GSLV.

Subtopics

GSLV Mk II Indian GSLV orbital launch vehicle variant.

GSLV-3 The Indian Geosynchronous Satellite Launch Vehicle Mark III was developed by ISRO to launch satellites into geostationary orbit and as a launcher for an Indian crew vehicle. The GSLV-3 featured an Indian cryogenic third stage and a higher payload capacity than the earlier GSLV models.

GSLV Mk.2C Indian GSLV orbital launch vehicle variant.

GSLV-0 N2O4/UDMH propellant rocket stage. .

GSLV-2 N2O4/UDMH propellant rocket stage. .

PSLV-2 N2O4/UDMH propellant rocket stage. .

Family: orbital launch vehicle. Country: India. Engines: RD-56M, Viking 2, Viking 4. Spacecraft: I-2K, Insat 3, GSat, Orbital Vehicle. Projects: Insat. Launch Sites: Sriharikota, Sriharikota PSLV, Sriharikota SLP. Stages: GSLV-0, GSLV-2, GSLV-3 stage, PSLV-1. Agency: ISRO. Bibliography: 2, 296, 42, 455, 61.

2001 April 18 - . 10:13 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. Launch Vehicle: GSLV.

GSAT-1 - . Payload: GramSat. Mass: 1,530 kg (3,370 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K. USAF Sat Cat: 26745 . COSPAR: 2001-015A. Apogee: 35,814 km (22,253 mi). Perigee: 33,825 km (21,017 mi). Inclination: 0.00 deg. Period: 1,387.00 min.
Experimental Rural Communications satellite. Launch delayed following pad abort on March 28. First launch of the Indian GSLV launch vehicle. GSat 1 was an Indian, 1500 kg scaled-dow) test model of a future geosynchronous communications spacecraft with a 440 N ISRO liquid apogee motor, and S-band and C-band ommunications transponders, similar to the Insat-2 satellites. The motor for the cryogenic, hydrogen-oxygen upper stage had been purchased from Russia but the design had never flown in space before. The stage cut off without providing the required delta-V - preliminary analysis revealed a shortfall of 0.5% in the thrust. An attempt was made to reach a usable orbit using the station-keeping motor of the GSAT satellite itself. After a series of burns, GSat 1 ran out of propellant - 10 kg more fuel would have been required to reach a stationary orbit. In the end, the parameters of the drifting (about 13 deg/day) orbit were period 23 hours, apogee 35,665 km, perigee 33,806 km, and inclination 0.99 deg. The fully functional transponders and transmitters on board were deactivated on instructions of the International Telecommunications Union. As of 4 September 2001 located at 54.88 deg E drifting at 13.212 deg E per day. As of 2007 Mar 10 located at 50.16W drifting at 12.778E degrees per day.

2003 May 8 - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. Launch Vehicle: GSLV.

GSAT-2 - . Payload: GramSat. Mass: 1,825 kg (4,023 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K. USAF Sat Cat: 27807 . COSPAR: 2003-018A. Apogee: 35,790 km (22,230 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Experimental Rural Communications. Launch delayed from original target of late 2001, then October 2002, then February 2003. The satellite carried four C-band transponders, two Ku-band transponders and a Mobile Satellite Service (MSS) payload operating in S-band and C-band for forward link and return link respectively. GSAT-2 also carried four piggyback experimental payloads: Total Radiation Dose Monitor (TRDM), Surface Charge Monitor (SCM), Solar X-ray Spectrometer (SOXS) and Coherent Radio Beacon Experiment (CRABEX). As of 2007 Mar 10 located at 47.97E drifting at 0.005E degrees per day.

2004 September 20 - . 10:31 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota PSLV. Launch Vehicle: GSLV.

GSAT-3 / Edusat - . Payload: GramSat. Mass: 1,950 kg (4,290 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K. USAF Sat Cat: 28417 . COSPAR: 2004-036A. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.10 deg. Period: 1,436.10 min.
Gsat-3 / Edusat was the first Indian satellite built exclusively for the educational sector. It was mainly intended to meet the demand for an interactive satellite based distance education system for India. Edusat was launched into a geosynchronous transfer orbit by its launch vehicle. Edusat was to reach geostationary orbit by firing, in stages, its on board Liquid Apogee Motor (LAM). In geostationary orbit the satellite was to be co-located with Kalpana-1 and Insat-3C satellites at 74 deg East longitude.
Compared to earlier satellites in the Insat series, Edusat used several new technologies. The spacecraft was built around the I-2K standardised spacecraft bus. It had a multiple spot beam antenna with a 1.2 m reflector to direct Ku band spot beams, a dual core bent heat pipe for thermal control, high efficiency multi-junction solar cells and an improved thruster configuration for optimised propellant use for orbit and orientation maintenance. The satellite used radiatively cooled Ku-band Travelling Wave Tube Amplifiers and a dielectrically loaded C-band demultiplexer for its communication payloads. Edusat carried five Ku-band transponders providing spot beams, one Ku-band transponder providing a national beam and six Extended C-band transponders with a national coverage beam. It was to join the Insat system that already provided more than 130 transponders in C-band, Extended C-band and Ku-band for a variety of telecommunication and television services.
First operational flight of launch vehicle. Launch delayed from July, August and September 10. Dry mass 820 kg. As of 2007 Mar 9 located at 73.92E drifting at 0.006W degrees per day.

2006 July 10 - . 12:08 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Vehicle: GSLV. FAILURE: One of the liquid-fueled strap-on motors failed to develop thrust. By 40 seconds after launch the GSLV had veered outside of the launch corridor and the destruct signal was sent.. Failed Stage: 0.

Insat 4C - . Mass: 2,168 kg (4,779 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K.

2007 September 2 - . 12:50 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Vehicle: GSLV.

Insat 4CR - . Mass: 2,130 kg (4,690 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K. USAF Sat Cat: 32050 . COSPAR: 2007-037A. Apogee: 35,790 km (22,230 mi). Perigee: 35,221 km (21,885 mi). Inclination: 0.10 deg. Period: 421.80 min. Ku-band television satellite..

2010 April 15 - . 10:57 GMT - . Launch Site: Sriharikota. LV Family: GSLV. Launch Vehicle: GSLV Mk II. FAILURE: Third stage failure..

Gsat 4 - . Nation: India. Agency: ISRO. Class: Communications. Type: Communications satellite. Spacecraft: I-2K. Failed to orbit due to third stage failure. Ka-band communications satellite with a GPS-augmentation navigation transmitter..

2010 December 25 - . 10:34 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Vehicle: GSLV. FAILURE: Destroyed at T+60 seconds after guidance commands from on-board computer to steering system of strapon boosters were cut off.. Failed Stage: 0.

Gsat 5P - . Mass: 2,310 kg (5,090 lb). Nation: India. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: I-2K. Vehicle reached only 15 km. First use of stretched cryogenic third state. Gsat-5P communications satellite destroyed..

2014 January 5 - . 10:48 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

GSAT-14 - . Mass: 1,982 kg (4,369 lb). Nation: India. Class: Communications. Type: Communications satellite. Spacecraft: I-2K. USAF Sat Cat: 39498 . COSPAR: 2014-001A. Apogee: 35,789 km (22,238 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.0800 deg. Period: 1,436.09 min.
Carried C and Ku band communications payloads, and Ka-band beacons for a propagation study. The launch vehicle put the satellite in an initial 182 km x 35,755 km x 19.4 deg geostationary transfer orbit. By January 7 its onboard apogee engine had placed it in a 32,543 x 35,741 km x 0.7 deg subsynchronous orbit on the way to GEO. By February 4 it was on station at 73.9 deg E.

2014 December 18 - . 04:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. Launch Pad: Srikarikota SLP. LV Family: GSLV. Launch Vehicle: GSLV-3.

CARE/LVM3-X - . Mass: 3,735 kg (8,234 lb). Nation: India. Class: Manned. Type: Manned spacecraft. Spacecraft: Indian Manned Spacecraft. Apogee: 126 km (78 mi).
Launch of the first GSLV-III rocket on a suborbital test flight. The S200 solid boosters and L110 core stage, with two Vikas engines, propelled an inert second stage to 126 km and 5.3 km/s. Second stage separation and payload separation were also tested; the payload was the Crew Module Atmospheric Reentry Experiment, a prototype command module for an Indian manned spacecraft with a mass of 3735 kg which splashed down in the Bay of Bengal. Orbit was around -4418 x 126 km x 32.7 deg.

2015 August 27 - . 11:22 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

GSAT-6 - . Mass: 2,117 kg (4,667 lb). Nation: India. Class: Communications. Type: Communications satellite. Spacecraft: I-2K. USAF Sat Cat: 40880 . COSPAR: 2015-041A. Apogee: 35,831 km (22,264 mi). Perigee: 35,742 km (22,209 mi). Inclination: 1.03 deg. Period: 1,436.10 min. Military communications satellite with S-band and C-band payload for use by the Indian Armed Forces. Geosynchronous orbit stationed at 83E.

2016 September 8 - . 11:20 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

Insat-3DR - . Nation: USA. Class: Earth. Type: Weather satellite. Spacecraft Bus: Insat 2. Spacecraft: Insat 3. USAF Sat Cat: 41752 . COSPAR: 2016-054A. Apogee: 35,935 km (22,328 mi). Perigee: 152 km (94 mi). Inclination: 20.60 deg.
Fourth GSLV Mk II rocket, carrying the Insat-3DR weather satellite. The cryogenic upper stage, serial CUS-07, performed nominally. The satellite made its first orbit raising burn on Sep 9. As well as weather sensors and data relay payloads, Insat-3DR carried a transponder to support search and rescue (SARSAT).

2017 May 5 - . 11:26 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

South Asia Satellite - . Payload: GSAT 9. Nation: India. USAF Sat Cat: 42695 . COSPAR: 2017-024A. Apogee: 35,798 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.12 deg. Period: 1,436.11 min. See GSat 9 (South Asian Satellite). ..

2017 June 5 - . 11:57 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV-3.

GSAT-19E - . Nation: India. USAF Sat Cat: 42747 . COSPAR: 2017-031A. Apogee: 35,805 km (22,248 mi). Perigee: 35,766 km (22,223 mi). Inclination: 0.0700 deg. Period: 1,436.05 min. See GSat 19. ..

2018 March 29 - . 11:25 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLP. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

GSAT 6A - . Nation: India. USAF Sat Cat: 43241 . COSPAR: 2018-027A. Apogee: 36,342 km (22,581 mi). Perigee: 26,007 km (16,159 mi). Inclination: 2.70 deg. Period: 1,207.03 min. See GSat 6A. ..

2018 November 14 - . 11:37 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota Dhawan SLP. LV Family: GSLV. Launch Vehicle: GSLV-3.

GSAT-29 - . Nation: India. Type: Comms. USAF Sat Cat: 43698 . COSPAR: 2018-089A. Apogee: 35,797 km (22,243 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.08 min. See GSat 29. ..

2018 December 19 - . 10:39 GMT - . Launch Site: Sriharikota. LV Family: GSLV. Launch Vehicle: GSLV Mk II.

GSAT-7A - . Nation: India. Type: Comms 1. USAF Sat Cat: 43864 . COSPAR: 2018-105A. Apogee: 35,796 km (22,242 mi). Perigee: 35,776 km (22,230 mi). Inclination: 0.0900 deg. Period: 1,436.07 min. See GSat 7A. ..

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