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SCE-200
The SCE-200, also referred as Semi-Cryogenic Engine, is a 2 MN thrust class liquid rocket engine, being developed to power India's future heavy and super heavy lift launch vehicles. It is being developed by Liquid Propulsion Systems Centre of Indian Space Research Organisation and is expected to have first flight in 2020s. Burning liquid oxygen (LOX) and RP-1 kerosene in an oxidizer-rich staged combustion cycle , the engine will boost payload capacity of India's existing LVM3 replacing current L110 stage powered by 2 Vikas engines. It is also expected to power ISRO's upcoming NGLV rockets (previously planned as ULV) as well as ISRO's future reusable rockets based on RLV technology demonstrations. The engine in September 2019 reportedly had become ready to begin testing in Ukraine and enter service no earlier than 2022. The use of engine of India's first human spaceflight, hence was ruled out by ISRO. By November 2022, SCE-200 had neared completion of its qualification ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
LVM3
The Launch Vehicle Mark-3 (LVM 3), previously referred to as the Geosynchronous Satellite Launch Vehicle Mark III (GSLV Mk3), is a three-stage medium-lift launch vehicle developed by the Indian Space Research Organisation (ISRO). Primarily designed to launch communication satellites into geostationary orbit, it is also due to launch crewed missions under the Indian Human Spaceflight Programme. GSLV Mk III has a higher payload capacity than it's predecessor, GSLV Mk II. After several delays and a sub-orbital test flight on 18 December 2014, ISRO successfully conducted the first orbital test launch of GSLV Mk III on 5 June 2017 from the Satish Dhawan Space Centre. Total development cost of project was . In June 2018, the Union Cabinet approved to build 10 GSLV Mk III rockets over a five-year period. The GSLV Mk III has launched CARE, India's space capsule recovery experiment module, Chandrayaan-2, India's second lunar mission, and will be used to carry Gaganyaan, the first crew ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Geosynchronous Satellite Launch Vehicle Mk III
The Launch Vehicle Mark-3 (LVM 3), previously referred to as the Geosynchronous Satellite Launch Vehicle Mark III (GSLV Mk3), is a three-stage medium-lift launch vehicle developed by the Indian Space Research Organisation (ISRO). Primarily designed to launch communication satellites into geostationary orbit, it is also due to launch crewed missions under the Indian Human Spaceflight Programme. GSLV Mk III has a higher payload capacity than it's predecessor, GSLV Mk II. After several delays and a sub-orbital test flight on 18 December 2014, ISRO successfully conducted the first orbital test launch of GSLV Mk III on 5 June 2017 from the Satish Dhawan Space Centre. Total development cost of project was . In June 2018, the Union Cabinet approved to build 10 GSLV Mk III rockets over a five-year period. The GSLV Mk III has launched CARE, India's space capsule recovery experiment module, Chandrayaan-2, India's second lunar mission, and will be used to carry Gaganyaan, the firs ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Indian Space Research Organisation
The Indian Space Research Organisation (ISRO; ) is the national space agency of India, headquartered in Bengaluru. It operates under the Department of Space (DOS) which is directly overseen by the Prime Minister of India, while the Chairman of ISRO acts as the executive of DOS as well. ISRO is India's primary agency for performing tasks related to space-based applications, space exploration and the development of related technologies. It is one of six government space agencies in the world which possess full launch capabilities, deploy cryogenic engines, launch extraterrestrial missions and operate large fleets of artificial satellites. The Indian National Committee for Space Research (INCOSPAR) was established by Jawaharlal Nehru under the Department of Atomic Energy (DAE) in 1962, on the urging of scientist Vikram Sarabhai, recognising the need in space research. INCOSPAR grew and became ISRO in 1969, within DAE. In 1972, the government of India set up a Space Commissi ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
ISRO
The Indian Space Research Organisation (ISRO; ) is the national space agency of India, headquartered in Bengaluru. It operates under the Department of Space (DOS) which is directly overseen by the Prime Minister of India, while the Chairman of ISRO acts as the executive of DOS as well. ISRO is India's primary agency for performing tasks related to space-based applications, space exploration and the development of related technologies. It is one of six government space agencies in the world which possess full launch capabilities, deploy cryogenic engines, launch extraterrestrial missions and operate large fleets of artificial satellites. The Indian National Committee for Space Research (INCOSPAR) was established by Jawaharlal Nehru under the Department of Atomic Energy (DAE) in 1962, on the urging of scientist Vikram Sarabhai, recognising the need in space research. INCOSPAR grew and became ISRO in 1969, within DAE. In 1972, the government of India set up a Space Commissio ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Unified Launch Vehicle
The Unified Launch Vehicle (ULV) is a family of modular expendable launch vehicles, currently under development by the Indian Space Research Organisation (ISRO). This vehicle is designed to replace the PSLV, GSLV Mk I/II and GSLV Mk III with a single family of launchers. The design may include a heavy-lift variant dubbed HLV, consisting of the SC-160 stage and two solid rocket boosters, as well as a super heavy-lift variant called SHLV with a cluster stage of five SCE-200 engines. As SCE-200 will only fly after the successful completion of the Gaganyaan program, the launcher will not fly before 2022. Design As of May 2013, based on ISRO data, the design comprised a common core and upper stage, with four different booster sizes. All four versions of the boosters are solid motors, with at least three versions reusing current motors from the PSLV, GSLV Mk I/II and LVM3. The core, known as the SC160 (Semi-Cryogenic stage with 160 tonnes of propellant, in the ISRO nomenclature), w ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-120
The RD-120 (GRAU Index 11D123) is a liquid upper stage rocket engine burning RG-1 (refined kerosene) and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine has been developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by, among others, Yuzhmash in Ukraine. It should not be confused with the RD-0120, which is a discontinued LOX/hydrogen rocket engine that was used in the Soviet Energia launch system. History During the Buran programme initial development of the 11D77 —the launch vehicle later known as Zenit—, KBKhA had been assigned the development of the second stage engine, as they had done for the Proton and Soyuz vehicles. But given the difficulties for NPO Energomash in developing the RD-123 (which ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Staged Combustion Cycle (rocket)
The staged combustion cycle (sometimes known as topping cycle, preburner cycle, or closed cycle) is a Liquid-propellant rocket#Engine cycles, power cycle of a bipropellant rocket Rocket engine, engine. In the staged combustion cycle, propellant flows through multiple Rocket engine#Combustion chamber, combustion chambers, and is thus combustion, combusted in stages. The main advantage relative to other rocket engine power cycles is high fuel efficiency, measured through specific impulse, while its main disadvantage is reliability engineering, engineering complexity. Typically, propellant flows through two kinds of combustion chambers; the first called preburner and the second called main combustion chamber. In the preburner, a small portion of propellant, usually fuel-rich, is partly combusted, and the increasing volume flow is used to drive the turbopumps that feed the engine with propellant. The gas is then injected into the main combustion chamber and combusted completely with ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-810
The RD-810 (РД-810) is a Ukrainian liquid propellant rocket engine burning LOX and Kerosene ( RG-1) in a staged combustion cycle. It has a single combustion chamber that provides thrust vector control by gimbaling of the nozzle in two axis by +/- 8°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family. The RD-810 as well as the RD-801 are being designed based on the work of the RD-8 vernier and the maintenance and improvement of the RD-120 engines. The RD-810 can be used stand alone on a Mayak or could be used in a module of four called RD-810M to replace the RD-170 on the Zenit. See also *Mayak – Prospective Ukrainian launch vehicle family for which the RD-810 is being developed. *RD-801 – A smaller engine of the same family designed by Yuzhnoe. *SCE-200 – An Indian rocket engine of equal specifications which might be based on the RD-810 blueprints. *Yuzhnoe Design Bureau – The RD-810 designe ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Staged Combustion Cycle
The staged combustion cycle (sometimes known as topping cycle, preburner cycle, or closed cycle) is a power cycle of a bipropellant rocket engine. In the staged combustion cycle, propellant flows through multiple combustion chambers, and is thus combusted in stages. The main advantage relative to other rocket engine power cycles is high fuel efficiency, measured through specific impulse, while its main disadvantage is engineering complexity. Typically, propellant flows through two kinds of combustion chambers; the first called preburner and the second called main combustion chamber. In the preburner, a small portion of propellant, usually fuel-rich, is partly combusted, and the increasing volume flow is used to drive the turbopumps that feed the engine with propellant. The gas is then injected into the main combustion chamber and combusted completely with the other propellant to produce thrust. Tradeoffs The main advantage is fuel efficiency due to all of the propellant flo ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
India
India, officially the Republic of India (Hindi: ), is a country in South Asia. It is the seventh-largest country by area, the second-most populous country, and the most populous democracy in the world. Bounded by the Indian Ocean on the south, the Arabian Sea on the southwest, and the Bay of Bengal on the southeast, it shares land borders with Pakistan to the west; China, Nepal, and Bhutan to the north; and Bangladesh and Myanmar to the east. In the Indian Ocean, India is in the vicinity of Sri Lanka and the Maldives; its Andaman and Nicobar Islands share a maritime border with Thailand, Myanmar, and Indonesia. Modern humans arrived on the Indian subcontinent from Africa no later than 55,000 years ago., "Y-Chromosome and Mt-DNA data support the colonization of South Asia by modern humans originating in Africa. ... Coalescence dates for most non-European populations average to between 73–55 ka.", "Modern human beings—''Homo sapiens''—originated in Africa. Then, int ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Russian Federal Space Agency
The State Space Corporation "Roscosmos" (russian: Государственная корпорация по космической деятельности «Роскосмос»), commonly known simply as Roscosmos (russian: Роскосмос), is a state corporation of the Russian Federation responsible for space flights, cosmonautics programs, and aerospace research. Originating from the Soviet space program founded in the 1950s, Roscosmos emerged following the dissolution of the Soviet Union in 1991. It initially began as the Russian Space Agency, which was established on 25 February 1992russian: Российское космическое агентство, ''Rossiyskoye kosmicheskoye agentstvo'', or RKA (russian: РКА). and restructured in 1999 and 2004, as the Russian Aviation and Space Agencyrussian: Российское авиационно-космическое агентство, ''Rossiyskoye aviatsionno-kosmicheskoye agentstvo'', commonly known as (rus ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Geostationary Transfer Orbit
A geosynchronous transfer orbit or geostationary transfer orbit (GTO) is a type of geocentric orbit. Satellite, Satellites that are destined for geosynchronous orbit, geosynchronous (GSO) or geostationary orbit (GEO) are (almost) always put into a GTO as an intermediate step for reaching their final orbit. A GTO is highly Elliptic orbit, elliptic. Its perigee (closest point to Earth) is typically as high as low Earth orbit (LEO), while its apogee (furthest point from Earth) is as high as geostationary (or equally, a geosynchronous) orbit. That makes it a Hohmann transfer orbit between LEO and GSO. Larson, Wiley J. and James R. Wertz, eds. Space Mission Design and Analysis, 2nd Edition. Published jointly by Microcosm, Inc. (Torrance, CA) and Kluwer Academic Publishers (Dordrecht/Boston/London). 1991. While some geostationary orbit, GEO satellites are launched direct to that orbit, often the launch vehicle lacks the power to put both the rocket and the satellite into that orbit. I ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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