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| Indian rocket |
Sounding
Sounding rockets are one or two-stage solid propellant rockets used for probing the upper atmospheric regions and for space research. They also serve as easily affordable platforms to test or prove prototypes of new components or subsystems intended for use in launch vehicles and satellites. With the establishment of the Thumba Equatorial Rocket Launching Station (TERLS) in 1963 at Thumba, a location close to the magnetic equator, there was a quantum jump in the scope for aeronomy and atmospheric sciences in India. The launch of the first sounding rocket from Thumba near Thiruvananthapuram, Kerala on 21 November 1963, marked the beginning of the Indian Space Programme. Sounding rockets made it possible to probe the atmosphere in situ using rocket-borne instrumentation. The first rockets were two-stage rockets imported from Russia (M-100) and France (Centaure). While the M-100 could carry a payload of 70 kg to an altitude of 85 km, the Centaure was capable of reaching 150 km with a payload of approximately 30 kg.
ISRO started launching indigenously made sounding rockets in 1965 The experience gained was of immense value in mastering solid propellant technology. In 1975, all sounding rocket activities were consolidated under the Rohini Sounding Rocket (RSR) Programme. RH-75, with a diameter of 75mm was the first truly Indian sounding rocket, which was followed by RH-100 and RH-125 rockets. The sounding rocket programme was the bedrock on which the edifice of launch vehicle technology in ISRO could be built. It is possible to conduct coordinated campaigns by simultaneously launching sounding rockets from different locations. It is also possible to launch several sounding rockets in a single day.
Operational sounding Rockets
Currently, three versions are offered as operational sounding rockets, which cover a payload range of 8-100 Kg and an apogee range of 80-475 km.
Vehicle RH-200 RH-300-Mk-II RH-560-MK-II
Payload (in kg) 10 60 100
Altitude (in km) 80 160 470
Purpose Meteorology Aeronomy Aeronomy
Launch Pad Thumba Balasore SDSC-SHAR SDSC-SHAR
Several scientific missions with national and international participation have been conducted using the Rohini sounding rockets.
SLV rocket
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| SLV ROCKET |
Satellite Launch Vehicle-3 (SLV-3) was India's first experimental satellite launch vehicle, which was an all solid, four-stage vehicle weighing 17 tonnes with a height of 22m and capable of placing 40 kg class payloads in Low Earth Orbit (LEO).
SLV-3
SLV-3 was successfully launched on July 18, 1980, from Sriharikota Range (SHAR), when Rohini satellite, RS-1, was placed in orbit, thereby making India the sixth member of an exclusive club of space-faring nations. SLV-3 employed open-loop guidance (with stored pitch programme) to steer the vehicle in flight along a pre-determined trajectory. The first experimental flight of SLV-3, in August 1979, was only partially successful. Apart from the July 1980 launch, two more launches were held in May 1981 and April 1983, orbiting Rohini satellites carrying remote sensing sensors.
The successful culmination of the SLV-3 project showed the way to advanced launch vehicle projects such as the Augmented Satellite Launch Vehicle (ASLV), Polar Satellite Launch Vehicle (PSLV) and the Geosynchronous Satellite Launch Vehicle (GSLV).
ASLV ROCKET
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| ASLV ROCKET |
ASLV
The Augmented Satellite Launch Vehicle (ASLV) Programme was designed to augment the payload capacity to 150 kg, thrice that of SLV-3, for Low Earth Orbits (LEO). While building upon the experience gained from the SLV-3 missions, ASLV proved to be a low-cost intermediate vehicle to demonstrate and validate critical technologies, that would be needed for future launch vehicles like strap-on technology, inertial navigation, bulbous heat shield, vertical integration and closed-loop guidance.
Under the ASLV programme, four developmental flights were conducted. The first developmental flight took place on March 24, 1987, and the second on July 13, 1988. The third developmental flight, ASLV-D3 was successfully launched on May 20, 1992, when SROSS-C (106 kg) was put into an orbit of 255 x 430 km. ASLV-D4 launched on May 4, 1994, orbited SROSS-C2 weighing 106 kg. It had two payloads, Gamma Ray Burst (GRB) Experiment and Retarding Potentio Analyser (RPA) and functioned for seven years.
POLAR SATELLITE LAUNCH VEHICLE OR PSLV ROCKET
Polar Satellite Launch Vehicle (PSLV) is the third generation launch vehicle of India. It is the first Indian launch vehicle to be equipped with liquid stages. After its first successful launch in October 1994, PSLV emerged as the reliable and versatile workhorse launch vehicle of India with 39 consecutively successful missions by June 2017. During the 1994-2017 period, the vehicle has launched 48 Indian satellites and 209 satellites for customers from abroad.
Besides, the vehicle successfully launched two spacecraft – Chandrayaan-1 in 2008 and Mars Orbiter Mission Spacecraft in 2013 – that later travelled to Moon and Mars respectively
Vehicle Specifications
Height: 44 m
Diameter: 2.8 m
Number of Stages: 4
Lift Off Mass: 320 tonnes (XL)
Variants : 3 (PSLV-G, PSLV - CA, PSLV - XL)
First Flight: September 20, 1993
PSLV Launcher
TECHNICAL SPECIFICATIONS
Payload to SSPO: 1,750 kg
PSLV earned its title 'the Workhorse of ISRO' through consistently delivering various satellites to Low Earth Orbits, particularly the IRS series of satellites. It can take up to 1,750 kg of payload to Sun-Synchronous Polar Orbits of 600 km altitude.
Payload to Sub GTO: 1,425 kg
Due to its unmatched reliability, PSLV has also been used to launch various satellites into Geosynchronous and Geostationary orbits, like satellites from the IRNSS constellation.
Fourth Stage: PS4
The PS4 is the uppermost stage of PSLV, comprising of two Earth storable liquid engines.
Engine : 2 x PS-4
Fuel : MMH + MON
Max. Thrust : 7.6 x 2 kN
Third Stage: PS3
The third stage of PSLV is a solid rocket motor that provides the upper stages high thrust after the atmospheric phase of the launch.
Fuel: HTPB
Max. Thrust: 240 kN
Second Stage: PS2
PSLV uses an Earth storable liquid rocket engine for its second stage, known as the Vikas engine, developed by Liquid Propulsion Systems Centre.
Engine: Vikas
Fuel : UDMH + N2O4
Max. Thrust: 799 kN
First Stage: PS1
PSLV uses the S139 solid rocket motor that is augmented by 6 solid strap-on boosters.
Engine: S139
Fuel: HTPB
Max. Thrust: 4800 kN
Strap-on Motors
PSLV uses 6 solid rocket strap-on motors to augment the thrust provided by the first stage in its PSLV-G and PSLV-XL variants. However, strap-ons are not used in the core alone version (PSLV-CA).
Fuel: HTPB
Max. Thrust: 719 kN
GEOSYNCHRONOUS SATELLITE LAUNCH VEHICLE or GSLV ROCKET
GSLV
About the Launch Vehicle
Geosynchronous Satellite Launch Vehicle Mark-II (GSLV Mk II) is the largest launch vehicle developed by India, which is currently in operation. This fourth-generation launch vehicle is a three-stage vehicle with four liquid strap-ons. The indigenously developed cryogenic Upper Stage (CUS), which is flight-proven, forms the third stage of GSLV Mk II. From January 2014, the vehicle has achieved four consecutive successes.
Vehicle Specifications
Height: 49.13 m
Number of Stages : 3
Lift Off Mass: 414.75 tonnes
First Flight: April 18, 2001
TECHNICAL SPECIFICATIONS
Payload to GTO: 2,500 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: 5,000 kg
Further, GSLV's capability of placing up to 5 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
Max. Thrust : 75 kN
Burn-time : 720 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 : UDMH + N2O4
Max. Thrust: 800 kN
Burntime: 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: 4700 kN
Burntime: 100 sec
Strap-on Motors
The four liquid engine strap-ons used in GSLV are heavier derivatives of PSLV's PS2 and use one Vikas engine each.
GSLV Mk III
About the Launch Vehicle
GSLV MkIII, chosen to launch Chandrayaan-2 spacecraft, is a three-stage heavy-lift launch vehicle developed by ISRO. The vehicle has two solid strap-ons, a core liquid booster and a cryogenic upper stage.
GSLV Mk III is designed to carry a 4 ton class of satellites into Geosynchronous Transfer Orbit (GTO) or about 10 tons to Low Earth Orbit (LEO), which is about twice the capability of the GSLV Mk II.
The two strap-on motors of GSLV Mk III are located on either side of its core liquid booster. Designated as ‘S200’, each carries 205 tons of composite solid propellant and their ignition results in vehicle lift-off. S200s function for 140 seconds. During the strap-ons functioning phase, the two clustered Vikas liquid Engines of the L110 liquid core booster will ignite 114 sec after lift-off to further augment the thrust of the vehicle. These two engines continue to function after the separation of the strap-ons at about 140 seconds after lift-off.
The first experimental flight of LVM3, the LVM3-X/CARE mission lifted off from Sriharikota on December 18, 2014, successfully tested the flight's atmospheric phase. Crew module Atmospheric Reentry Experiment was also carried out in this flight. The module reentered, deployed its parachutes as planned and splashed down in the Bay of Bengal.
The first developmental flight of GSLV Mk III, the GSLV-Mk III-D1 successfully placed the GSAT-19 satellite to a Geosynchronous Transfer Orbit (GTO) on June 05, 2017, from SDSC SHAR, Sriharikota.
GSLV MkIII-D2, the second developmental flight of GSLV MkIII successfully launched GSAT-29, a high throughput communication satellite on November 14, 2018, from Satish Dhawan Space Centre SHAR, Sriharikota
GSLV MkIII-M1, successfully injected Chandrayaan-2, India’s second Lunar Mission, into Earth Parking Orbit on July 22, 2019, from Satish Dhawan Space Centre SHAR, Sriharikota
Specifications
Height: 43.43 m
Vehicle Diameter: 4.0 m
Heat Shield (Payload Fairing) Diameter: 5.0 m
Number of Stages : 3
Lift Off Mass: 640 tonnes
GSLV Mk III
TECHNICAL SPECIFICATIONS
Payload to GTO: 4,000 kg
Payload to GTO: 4,000 kg
GSLV Mk III will be capable of placing the 4-tonne class satellites of the GSAT series into Geosynchronous Transfer Orbits.
Payload to LEO: 8,000 kg
Payload to LEO: 8,000 kg
The powerful cryogenic stage of GSLV Mk III enables it to place heavy payloads into Low Earth Orbits of 600 km altitude.
Cryogenic Upper Stage: C25
Cryogenic Upper Stage: C25
The C25 is powered by CE-20, India's largest cryogenic engine, designed and developed by the Liquid Propulsion Systems Centre.
Cryo Stage Height: 13.5 m
Cryo Stage Diameter: 4.0 m
Engine: CE-20
Fuel : 28 tonnes of LOX + LH2
Solid Rocket Boosters: S200
GSLV Mk III uses two S200 solid rocket boosters to provide the huge amount of thrust required for lift-off. The S200 was developed at Vikram Sarabhai Space Centre.
Booster Height: 25 m
Booster Diameter: 3.2 m
Fuel: 205 tonnes of HTPB (nominal)
Core Stage: L110 Liquid Stage
Core Stage: L110 Liquid Stage
The L110 liquid stage is powered by two Vikas engines designed and developed at the Liquid Propulsion Systems Centre.
Stage Height: 21 m
Stage Diameter: 4 m
Engine: 2 x Vikas
Fuel: 110 tonnes of UDMH + N2O4
Fuel : UDMH + N2O4
Max. Thrust: 680 kN
Burntime: 160 sec
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