Engineering:Geosynchronous Satellite Launch Vehicle

Short description: Class of Indian medium-lift expendable launch vehicles, developed by ISRO

GSLV

GSLV-F10 carrying GISAT-1 at the Satish Dhawan Space Centre Second Launch Pad
Function	Medium-lift Launch System
Manufacturer	ISRO
Country of origin	India
Cost per launch	US$47 million
Size
Height	49.13 m (161.2 ft)
Diameter	2.8 m (9 ft 2 in)
Mass	414,750 kg (914,370 lb)
Stages	3
Capacity
Payload to LEO	6,000 kg (13,000 lb)
Payload to SSO	3,000 kg (6,600 lb)
Payload to GTO	2,500 kg (5,500 lb)
Launch history
Status	Mk I: Retired Mk II: Active
Launch sites	Satish Dhawan Space Centre
Total launches	15
Successes	9
Failures	4
Partial failures	2
First flight	Mk.I: 18 April 2001 Mk.II: 15 April 2010
Last flight	Mk.I: 25 December 2010 Mk.II: 29 May 2023
Notable payloads	South Asia Satellite, NavIC
Boosters
No. boosters	4 L40 Hs
Length	19.7 m (65 ft)
Diameter	2.1 m (6 ft 11 in)
Propellant mass	42,700 kg (94,100 lb) each
Engines	1 L40H Vikas 2
Thrust	760 kN (170,000 lbf)
Total thrust	3,040 kN (680,000 lbf)
Specific impulse	262 s (2.57 km/s)
Burn time	154 seconds
Fuel	N2O4 / UDMH
First stage
Length	20.2 m (66 ft)
Diameter	2.8 m (9 ft 2 in)
Propellant mass	138,200 kg (304,700 lb)
Engines	1 S139 Booster
Thrust	4,846.9 kN (1,089,600 lbf)
Specific impulse	237 s (2.32 km/s)
Burn time	100 seconds
Fuel	HTPB (solid)
Second stage
Length	11.6 m (38 ft)
Diameter	2.8 m (9 ft 2 in)
Propellant mass	39,500 kg (87,100 lb)
Engines	1 GS2 Vikas 4
Thrust	846.8 kN (190,400 lbf)
Specific impulse	295 s (2.89 km/s)
Burn time	139 seconds
Fuel	N2O4 / UDMH
Second GS2 (GL40) stage
Length	11.9 m (39 ft)
Diameter	2.8 m (9 ft 2 in)
Propellant mass	42,500 kg (93,700 lb)
Engines	1 GS2 Vikas 4
Thrust	846.8 kN (190,400 lbf)
Specific impulse	295 s (2.89 km/s)
Burn time	149 seconds
Fuel	N2O4 / UDMH
Third stage (GSLV Mk I) – CUS
Length	N/A
Diameter	2.8 m (9 ft 2 in)
Propellant mass	N/A
Engines	1 KVD-1
Thrust	70 kN (16,000 lbf)
Specific impulse	462 s (4.53 km/s)
Burn time	N/A
Fuel	LOX / LH2
Third stage (GSLV Mk II) – CUS12
Length	8.7 m (29 ft)
Diameter	2.8 m (9 ft 2 in)
Propellant mass	12,800 kg (28,200 lb)
Engines	1 CE-7.5
Thrust	75 kN (17,000 lbf)
Specific impulse	454 s (4.45 km/s)
Burn time	718 seconds
Fuel	LOX / LH2
Third stage (GSLV Mk II) – CUS15
Length	9.9 m (32 ft)
Diameter	2.8 m (9 ft 2 in)
Propellant mass	15,000 kg (33,000 lb)
Engines	1 CE-7.5
Thrust	75 kN (17,000 lbf)
Specific impulse	454 s (4.45 km/s)
Burn time	846 seconds
Fuel	LOX / LH2

Geosynchronous Satellite Launch Vehicle (GSLV) is a class of expendable launch systems operated by the Indian Space Research Organisation (ISRO). GSLV has been used in fifteen launches since 2001.

History

The Geosynchronous Satellite Launch Vehicle (GSLV) project was initiated in 1990 with the objective of acquiring an Indian launch capability for geosynchronous satellites.

GSLV uses major components that are already proven in the Polar Satellite Launch Vehicle (PSLV) launch vehicles in the form of the S125/S139 solid rocket booster and the liquid-fueled Vikas engine. Due to the thrust required for injecting the satellite in a geostationary transfer orbit (GTO) the third stage was to be powered by a LOX/LH2 Cryogenic engine which at that time India did not possess or have the technological expertise to build.

Indigenous Cryogenic Upper Stage CE-7.5 of GSLV

The first development flight of the GSLV (Mk I configuration) was launched on 18 April 2001 was a failure as the payload failed to reach the intended orbit parameters. The launcher was declared operational after the second development flight successfully launched the GSAT-2 satellite. During the initial years from the initial launch to 2014 the launcher had a checkered history with only 2 successful launches out of 7.

Cryogenic engine controversy

The third stage was to be procured from Russian company Glavkosmos, including transfer of technology and design details of the engine based on an agreement signed in 1991. Russia backed out of the deal after United States objected to the deal as in violation of the Missile Technology Control Regime (MTCR) in May 1992. As a result, ISRO initiated the Cryogenic Upper Stage Project in April 1994 and began developing its own cryogenic engine. A new agreement was signed with Russia for 7 KVD-1 cryogenic stages and 1 ground mock-up stage with no technology transfer, instead of 5 cryogenic stages along with the technology and design as per the earlier agreement. These engines were used for the initial flights and were named GSLV Mk I.

Vehicle description

The 49 m (161 ft) tall GSLV, with a lift-off mass of 415 t (408 long tons; 457 short tons), is a three-stage vehicle with solid, liquid and cryogenic stages respectively. The payload fairing, which is 7.8 m (26 ft) long and 3.4 m (11 ft) in diameter, protects the vehicle electronics and the spacecraft during its ascent through the atmosphere. It is discarded when the vehicle reaches an altitude of about 115 km (71 mi).

GSLV employs S-band telemetry and C-band transponders for enabling vehicle performance monitoring, tracking, range safety / flight safety and preliminary orbit determination. The Redundant Strap Down Inertial Navigation System/Inertial Guidance System of GSLV housed in its equipment bay guides the vehicle from lift-off to spacecraft injection. The digital auto-pilot and closed loop guidance scheme ensure the required altitude maneuver and guide injection of the spacecraft to the specified orbit.

The GSLV can place approximately 5,000 kg (11,000 lb) into an easterly low Earth orbit (LEO) or 2,500 kg (5,500 lb) (for the Mk II version) into an 18° geostationary transfer orbit.

Strap-on motors of GSLV-F05 being integrated with the core stage

Liquid boosters

The first GSLV flight, GSLV-D1 used the L40 stage. Subsequent flights of the GSLV used high pressure engines in the strap-on boosters called the L40H. The GSLV uses four L40H liquid strap-on boosters derived from the L37.5 second stage, which are loaded with 42.6 tons of hypergolic propellants (UDMH and N₂O₄). The propellants are stored in tandem in two independent tanks 2.1 m (6 ft 11 in) diameter. The engine is pump-fed and generates 760 kN (170,000 lb_f) of thrust, with a burn time of 150 seconds.

First stage

GSLV-D1 used the S125 stage which contained 125 t (123 long tons; 138 short tons) of solid propellant and had a burn time of 100 seconds. All subsequent launches have used enhanced propellant loaded S139 stage. The S139 stage is 2.8 m in diameter and has a nominal burn time of 100 seconds.

Hoisting of the GSLV-F09 second stage during vehicle integration.

Second stage

The GS2 stage is powered by the Vikas engine. It has a diameter of 2.8 m (9 ft 2 in).

Third stage

The third stage of the GSLV Mark II is propelled by the Indian CE-7.5 cryogenic rocket engine while the older defunct Mark I is propelled using a Russian made KVD-1. It uses liquid hydrogen (LH2) and liquid oxygen (LOX) The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre The engine has a default thrust of 75 kN (17,000 lb_f) but is capable of a maximum thrust of 93.1 kN (20,900 lb_f).

Payload fairing with GSAT-6A being integrated.

Variants

GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mark I while versions using the indigenous Cryogenic Upper Stage (CUS) are designated the GSLV Mark II. All GSLV launches have been conducted from the Satish Dhawan Space Centre in Sriharikota.

GSLV Mark I

The first developmental flight of GSLV Mark I had a 129 tonne (S125) first stage and was capable of launching around 1500 kg into geostationary transfer orbit. The second developmental flight replaced the S125 stage with S139. It used the same solid motor with 138 tonne propellant loading. The chamber pressure in all liquid engines were enhanced, enabling a higher propellant mass and burn time. These improvements allowed GSLV to carry an additional 300 kg of payload. The fourth operational flight of GSLV Mark I, GSLV-F06, had a longer third stage called the C15 with 15 tonne propellant loading and also employed a 4 meter diameter payload fairing.

Launch of GSLV F11 GSAT-7A from Second Launch Pad of Satish Dhawan Space Centre

GSLV Mark II

This variant uses an Indian cryogenic engine, the CE-7.5, and is capable of launching 2500 kg into geostationary transfer orbit. Previous GSLV vehicles (GSLV Mark I) have used Russian cryogenic engines.

For launches from 2018, a 6% increased thrust version of the Vikas engine was developed. It was demonstrated on 29 March 2018 in the GSAT-6A launch second stage. It was used for the four Vikas engines first stage boosters on future missions.

A 4m diameter Ogive payload fairing was developed and deployed for the first time in the EOS-03 launch on 12 August 2021, although this launch was a failure due to technical anomalies with the Cryogenic Upper Stage. This will allow GSLV vehicles to accommodate larger payloads.

Launch statistics

Launch system status

  Active

  Retired

Variant	Launches	Successes	Failures	Partial failures
GSLV Mk. I	6	2	2	2
GSLV Mk. II	9	7	2	0
Total (As of May 2023)	15	9	4	2

Decade-wise summary of GSLV Launches

Decade	Successful	Partial success	Failure	Total
2000s	2	2	1	5
2010s	6	0	2	8
2020s	1	0	1	2
Total	9	2	4	15

Gallery

• 

  GSLV F05 take off

• 

  GSLV F11 vehicle at Second Launch Pad.

• 

  Fully integrated GSLV-F05 coming out of the Vehicle Assembly Building.

• 

  Launch of GSLV F11 from Second Launch Pad.

• 

  Top view of a fully Integrated GSLV-F08 inside the Vehicle Assembly Building.

See also

• Comparison of orbital launchers families
• Comparison of orbital launch systems
• PSLV
• LVM3
• NGLV
• ISRO
• ASLV
• SLV

External links

• ISRO GSLV Page
• INDIA in Space – GSLV Page
• 12KRB (KVD-1) Upper Stage at Khrunichev Space Center