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GSLV
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 $: 500.000 million. Launch Price $: 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.1 (2) Indian GSLV orbital launch vehicle variant.

GSLV Mk II Indian GSLV orbital launch vehicle variant.

GSLV Mk.1 (3) 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.

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