An expendable launch system (or expendable launch vehicle/ELV ) is a launch vehicle that can be launched only once, after which its components are either destroyed during reentry or discarded in space. ELVs typically consist of several rocket stages that are discarded sequentially as their fuel is exhausted and the vehicle gains altitude and speed. As of 2024, fewer and fewer satellites and human spacecraft are launched on ELVs in favor of reusable launch vehicles . However, there are many instances where a ELV may still have a compelling use case over a reusable vehicle. ELVs are simpler in design than reusable launch systems and therefore may have a lower production cost. Furthermore, an ELV can use its entire fuel supply to accelerate its payload, offering greater payloads. ELVs are proven technology in widespread use for many decades.
36-527: 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. 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
72-596: A staged combustion cycle was adopted for the first stage engine, the LE-7 . The combination of the liquid hydrogen two-stage combustion cycle first stage engine and solid rocket boosters was carried over to its successor, the H-IIA and H-IIB and became the basic configuration of Japan's liquid fuel launch vehicles for 30 years, from 1994 to 2024. In 2003, JAXA was formed by merging Japan's three space agencies to streamline Japan's space program, and JAXA took over operations of
108-565: 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 ). In GSLV-F14 mission, a new white coloured C15 stage was introduced which has more environmental-friendly manufacturing processes, better insulation properties and the use of lightweight materials. GSLV rockets using the Russian Cryogenic Stage (CS) are designated as the GSLV Mark I while versions using
144-644: A joint venture between Airbus and Safran . European space launches are carried out as a collaborative effort between private companies and government agencies. The role of Arianespace is to market Ariane 6 launch services, prepare missions, and manage customer relations. At the Guiana Space Centre (CSG) in French Guiana , the company oversees the team responsible for integrating and preparing launch vehicles. The rockets themselves are designed and manufactured by other companies: ArianeGroup for
180-552: A sounding rocket in the 1960s and 1970s and advanced its research to deliver the Satellite Launch Vehicle-3 and the more advanced Augmented Satellite Launch Vehicle (ASLV), complete with operational supporting infrastructure by the 1990s. Japan launched its first satellite, Ohsumi , in 1970, using ISAS' L-4S rocket. Prior to the merger, ISAS used small Mu rocket family of solid-fueled launch vehicles, while NASDA developed larger liquid-fueled launchers. In
216-527: A two-thrust chambered, step-throttled second stage, the SLV has a lift off mass exceeding 26 tons. The first stage consists of a lengthened up-rated Shahab-3C . According to the technical documentation presented in the annual meeting of the United Nations Office for Outer Space Affairs , it is a two-stage rocket with all liquid propellant engines. The first stage is capable of carrying the payload to
252-471: Is pump-fed and generates 760 kN (170,000 lb f ) of thrust, with a burn time of 150 seconds. 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. The GS2 stage
288-545: Is a family of hypergolic liquid fuelled rocket engines conceptualized and designed by the Liquid Propulsion Systems Centre in the 1970s. The design was based on the licensed version of the Viking engine with the chemical pressurisation system. The early production Vikas engines used some imported French components which were later replaced by domestically produced equivalents. It is used in
324-803: Is a prototype spaceplane concept created by ISRO. For the Orbital return Flight experiment, a modified version of the GSLV mk.II launcher, with the upper Cryogenic Stage replaced with the PS-4 stage from the PSLV is currently in development,as the RLV won't need all the excess energy produced by the CUS . As of 17 February 2024, rockets from the GSLV family have made 16 launches, resulting in 10 successes, four failures, and two partial failures. All launches have occurred from
360-679: Is powered by the Vikas engine . It has a diameter of 2.8 m (9 ft 2 in). 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 (LH 2 ) and liquid oxygen (LOX) The Indian cryogenic engine was built at the Liquid Propulsion Systems Centre The engine has
396-684: The H-IIA liquid-fueled launch vehicle, the M-V solid-fuel launch vehicle, and several observation rockets from each agency. The H-IIA is a launch vehicle that improved reliability while reducing costs by making significant improvements to the H-II, and the M-V was the world's largest solid-fuel launch vehicle at the time. In November 2003, JAXA's first launch after its inauguration, H-IIA No. 6, failed, but all other H-IIA launches were successful, and as of February 2024,
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#1732787839091432-579: The International Space Station . To be able to launch smaller mission on JAXA developed a new solid-fueled rocket, the Epsilon as a replacement to the retired M-V . The maiden flight successfully happened in 2013. So far, the rocket has flown six times with one launch failure. In January 2017, JAXA attempted and failed to put a miniature satellite into orbit atop one of its SS520 series rockets. A second attempt on 2 February 2018
468-590: 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 / LH 2 Cryogenic engine which at that time India did not possess or have the technological expertise to build. The aerodynamic characterization research
504-601: The Polar Satellite Launch Vehicle (PSLV), Geosynchronous Satellite Launch Vehicle (GSLV) and LVM3 for space launch use. Vikas engine is used to power the second stage of PSLV, boosters and second stage of GSLV Mark I and II and also the core stage of LVM3. The propellant loading for Vikas engine in PSLV, GSLV Mark I and II is 40 tons, while in LVM3 is 55 tons. In 1974, Societe Europeenne de Propulsion agreed to transfer Viking engine technology in return for 100 man-years of engineering work from ISRO. The first engine built from
540-511: The United Launch Alliance . The National Security Space Launch (NSSL) competition has selected two EELV successors, the expendable Vulcan Centaur and partially reusable Falcon 9 , to provide assured access to space. Iran has developed an expendable satellite launch vehicle named Safir SLV . Measuring 22 m in height with a core diameter of 1.25 m, with two liquid propellant stages, a single thrust chambered first stage and
576-678: The Ariane 6 and Avio for the Vega. The launch infrastructure at the CSG is owned by the European Space Agency , while the land itself belongs to and is managed by CNES , the French national space agency. During the 1960s and 1970s, India initiated its own launch vehicle program in alignment with its geopolitical and economic considerations. In the 1960sā1970s, the country India started with
612-602: 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
648-614: The H-IIA had successfully launched 47 of its 48 launches. JAXA plans to end H-IIA operations with H-IIA Flight No. 50 and retire it by March 2025. JAXA operated the H-IIB , an upgraded version of the H-IIA, from September 2009 to May 2020 and successfully launched the H-II Transfer Vehicle six times. This cargo spacecraft was responsible for resupplying the Kibo Japanese Experiment Module on
684-557: 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 N 2 O 4 ). The propellants are stored in tandem in two independent tanks 2.1 m (6 ft 11 in) diameter. The engine
720-645: The Ofek satellites on September 19, 1988; April 3, 1990; and April 5, 1995. The Shavit launchers allows low-cost and high-reliability launch of micro/mini satellites to a low Earth orbit . The Shavit launcher is developed by Malam factory, one of four factories in the IAI Electronics Group. The factory is very experienced in development, assembling, testing and operating system for use in space. Vikas (rocket engine) The Vikas (a portmanteau from initials of VIK ram A mbalal S arabhai )
756-603: The Satish Dhawan Space Centre, known before 2002 as the Sriharikota Range (SHAR). Expendable launch systems Arianespace SA is a French company founded in March 1980 as the world's first commercial launch service provider . It operates two launch vehicles : Vega C , a small-lift rocket , and Ariane 6 , a medium -to- heavy-lift rocket. Arianespace is a subsidiary of ArianeGroup ,
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#1732787839091792-659: The United States purchase ELV launches. NASA is a major customer with the Commercial Resupply Services and Commercial Crew Development programs, also launching scientific spacecraft. The vast majority of launch vehicles for its missions, from the Redstone missile to the Delta , Atlas , Titan and Saturn rocket families, have been expendable. As its flagship crewed exploration replacement for
828-431: The acquired technology was tested successfully in 1985 by Nambi Narayanan and his team at ISRO and named it Vikas. The engine uses up about 40 metric tons of UDMH as fuel and Nitrogen tetroxide (N 2 O 4 ) as oxidizer with a maximum thrust of 725 kN. An upgraded version of the engine has a chamber pressure of 58.5 bar as compared to 52.5 bar in the older version and produces a thrust of 800 kN. The engine
864-562: The beginning, NASDA used licensed American models. The first model of liquid-fueled launch vehicle developed domestically in Japan was the H-II , introduced in 1994. NASDA developed the H-II with two goals in mind: to be able to launch satellites using only its own technology, such as the ISAS, and to dramatically improve its launch capability over previous licensed models. To achieve these two goals,
900-684: 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
936-421: The earlier agreement. These engines were used for the initial flights and were named GSLV Mk I. 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
972-551: 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 . 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
1008-403: The initial launch to 2014 the launcher had a checkered history with only 2 successful launches out of 7, resulting in the rocket gaining the nickname "naughty boy". 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
1044-508: The maximum altitude of 68 kilometres. The Israel Space Agency is one of only seven countries that both build their own satellites and launch their own launchers. The Shavit is a space launch vehicle capable of sending payload into low Earth orbit . The Shavit launcher has been used to send every Ofeq satellite to date. The development of the Shavit began in 1983 and its operational capabilities were proven on three successful launches of
1080-626: The partially reusable Space Shuttle , NASA's newest ELV, the Space Launch System flew successfully in November 2022 after delays of more than six years. It is planned to serve in a major role on crewed exploration programs going forward. The United States Air Force is also an ELV customer, having designed the Titan, Atlas, and Delta families. The Atlas V from the 1994 Evolved ELV (EELV) program remains in active service, operated by
1116-523: 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. This variant uses an Indian cryogenic engine,
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1152-445: 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
1188-503: 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 18Ā° geostationary transfer orbit . The first GSLV flight, GSLV-D1 used
1224-549: Was conducted at the National Aerospace Laboratories ' 1.2m Trisonic Wind Tunnel Facility. 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
1260-593: 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. As of October 2024, ISRO has stopped selling GSLV Mk II Rockets. Eight Known launches are planned with NVS Missions, IDRSS Missions, NISAR Mission,etc. The Reusable Launch Vehicle Technology Demonstration program ,
1296-667: Was successful, putting a four kilogram CubeSat into Earth orbit. The rocket, known as the SS-520-5, is the world's smallest orbital launcher. Roscosmos uses a family of several launch rockets, the most famous of them being the R-7 , commonly known as the Soyuz rocket that is capable of launching about 7.5 tons into low Earth orbit (LEO). The Proton rocket (or UR-500K) has a lift capacity of over 20 tons to LEO. Smaller rockets include Rokot and other Stations. Several governmental agencies of
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