Geosynchronous Satellite Launch Vehicle Mark II
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PSLV Launcher
Payload Fairing There are two variant of payload fairing for GSLV vehicle:
1. Diameter of 3.4 m metallic PLF &
2. Diameter of 4 m ogive PLF.
The payload fairing of GSLV is wider than the rest of the launcher. The fairing provides aerodynamic efficiency and shields the payload from mechanical damage during the atmospheric phase of flight.
CUS(Third Stage) The cryogenic upper stage of GSLV imparts a high velocity to the payload and detaches at the periapsis. This high velocity is characteristic of the Geosynchronous Transfer Orbit. Once the spacecraft reaches the apoapsis of this high eccentricity orbit, it performs a burn using its Spacecraft propulsion to circularise its orbit.
GS2(Second Stage) The high thrust hypergolic liquid propellant Vikas engine's newer improved version with a higher chamber pressure is used here. It is activated 150 seconds into flight.
S139 (First Stage):
The first stage of GSLV is ignited at Lift off(To) after the ignition of the four strap-ons occurring at (To-4.8 sec), ensuring their full functionality. This is required in order to extract maximum thrust out of the initial stages. The solid core of the first stage burns for 100 seconds while the strap-ons continue to provide thrust for another 40 seconds
L40 (Strap-on Boosters
The GSLV uses 4 liquid strap-on motors. The strap-ons are powered by one Vikas engine each and along with the solid rocket motor core of the first stage, provide an enormous thrust to the launcher.

Vehicle Specifications

Height : 51.73 m (With Ogive PLF)
Number of Stages : 3
Lift Off Mass : 420 tonnes
First Flight : April 18, 2001
First Flight (With Indigenous Cryo Stage) : January 5, 2014

Technical Specification

Payload to GTO: 2,250 kg

GSLV's primary payloads are INSAT class of communication satellites that operate from Geostationary orbits and hence are placed in Geosynchronous Transfer Orbits by GSLV.

Payload to LEO (Low Earth Orbit) : 6,000 kg

Further, GSLV's capability of placing up to 6 tonnes in Low Earth Orbits broadens the scope of payloads from heavy satellites to multiple smaller satellites.

Third Stage: CUS

Developed under the Cryogenic Upper Stage Project (CUSP), the CE-7.5 is India's first cryogenic engine, developed by the Liquid Propulsion Systems Centre. CE-7.5 has a staged combustion operating cycle.

Fuel : LOX + LH2
Nominal Thrust (Max) : 75 kN
Burn-time : 814 sec

Second Stage: GS2

One Vikas engine is used in the second stage of GSLV. The stage was derived from the PS2 of PSLV where the Vikas engine has proved its reliability

Engine : Vikas
Fuel : UH25 + N2O4
Nominal Thrust (Max) : 846 kN
Burn-time : 150 sec

First Stage: GS1

The first stage of GSLV was also derived from the PSLV's PS1. The 138 tonne solid rocket motor is augmented by 4 liquid strap-ons.

Engine : S139
Fuel : HTPB
Max. Thrust : 4800 kN
Burn-time : 100 sec

About the Launch Vehicle

Geosynchronous Satellite Launch Vehicle Mark II (GSLV Mk II) is the launch vehicle developed by India, to launch communication satellites in geo transfer orbit using cryogenic third stage. Initially Russian GK supplied cryogenic stages were used. Later cryogenic stage was indigenously developed and inducted in Jan 2014 from GSLV D5 onwards. This operational fourth generation launch vehicle is a three stage vehicle with four liquid strap-ons. The flight proven indigenously developed Cryogenic Upper Stage (CUS), forms the third stage of GSLV Mk II. From January 2014, the vehicle has achieved six consecutive successes

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