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SCE-200
The SCE-200 which was recently renamed by ISRO as, SE-2000 (also referred as Semi-Cryogenic Engine-2000) is a 2 MN thrust class liquid rocket engine, being developed to power Indian Space Research Organisation's (ISRO) existing LVM3 and upcoming heavy and super heavy-lift launch vehicles. It is being developed by the Liquid Propulsion Systems Centre (LPSC) of ISRO, 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 LVM3 replacing current L110 stage powered by 2 Vikas engines. It is also expected to power ISRO's upcoming Next Generation Launch Vehicle (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 spacefli ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Next Generation Launch Vehicle
The Next Generation Launch Vehicle (NGLV) is a family of three-stage Reusable launch vehicle#Partially reusable launch systems, partially reusable Medium-lift launch vehicle, medium to super heavy-lift launch vehicle, currently under development by the ISRO, Indian Space Research Organisation (ISRO). The family of these vehicles are designed to replace currently operational systems like the Polar Satellite Launch Vehicle, PSLV and Geosynchronous Satellite Launch Vehicle, GSLV. Previously referred to as Unified Launch Vehicle (ULV), the project is now being called as project Soorya. This family of three launchers were previously being designed for replacing the different core propulsion modules of PSLV, GSLV, and LVM3 respectively with a common semi-cryogenic engine and hence it was named as ULV. Unlike the latest proposal of the launcher, the initial proposals were planned to be Expendable launch system, expendable. But the new proposals under the name of NGLV suggests launcher ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Unified Launch Vehicle
The Next Generation Launch Vehicle (NGLV) is a family of three-stage partially reusable medium to super heavy-lift launch vehicle, currently under development by the Indian Space Research Organisation (ISRO). The family of these vehicles are designed to replace currently operational systems like the PSLV and GSLV. Previously referred to as Unified Launch Vehicle (ULV), the project is now being called as project Soorya. This family of three launchers were previously being designed for replacing the different core propulsion modules of PSLV, GSLV, and LVM3 respectively with a common semi-cryogenic engine and hence it was named as ULV. Unlike the latest proposal of the launcher, the initial proposals were planned to be expendable. But the new proposals under the name of NGLV suggests launchers having partial reusability. S. Sivakumar is the program director for ISRO's Space Transportation System and the projector director for NGLV at the Vikram Sarabhai Space Centre (VSSC). The ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
LVM3
The Launch Vehicle Mark-3 or LVM3 (previously referred as the Geosynchronous Satellite Launch Vehicle Mark III or GSLV Mk III) is a Multistage rocket, three-stage medium-lift launch vehicle developed by the ISRO, 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. LVM3 has a higher payload capacity than its predecessor, Geosynchronous Satellite Launch Vehicle, GSLV. After several delays and a sub-orbital test flight on 18 December 2014, ISRO successfully conducted the first orbital test launch of LVM3 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 LVM3 rockets over a five-year period. The LVM3 has launched Crew Module Atmospheric Re-entry Experiment, CARE, India's space capsule recovery experiment module, Chandrayaan-2 and Ch ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
ISRO Propulsion Complex
The ISRO Propulsion Complex (IPRC), located at Mahendragiri in Tamil Nadu, is an Indian Space Research Organisation (ISRO) centre involved in testing, assembling, and integrating propulsion systems and stages that are developed at ISRO's Liquid Propulsion Systems Centres (LPSC). Formerly, IPRC was known as LPSC, Mahendragiri, functioning under LPSC. It was elevated as an independent centre and renamed as IPRC with effect from 1 February 2014. The complex is situated near Panagudi in Tirunelveli District, Tamil Nadu. It is one of the ISRO centres that could be called as the "Jet Propulsion Laboratory of India" as all liquid, cryogenic and semicryogenic stage and engine related tests of ISRO's launch vehicles and satellites are carried out here. Capabilities Following activities are currently carried out at IPRC: *Assembly, integration and testing of launch vehicle motors and stages *Servicing of launch vehicle motors and stages *Propellant storage *Sea level and high alti ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-120
The RD-120 (, GRAU index: 11D123) is a Liquid-propellant rocket, liquid upper stage rocket engine burning RG-1 (propellant), RG-1 (refined kerosene) and LOX in an Staged combustion cycle (rocket), oxidizer rich staged combustion cycle with an Rocket propellant#Mixture ratio, O/F ratio of 2.6. It is used in the second stage of the Zenit (rocket family), 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 thruster, vernier engine. The engine was 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 (rocket), Energia launch system. History During the Buran programme initial development of the 11D77 —the launch vehicle later known as Zenit (rocket family), Zenit—, Chemical ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
ISRO
The Indian Space Research Organisation (ISRO ) is India's national space agency, headquartered in Bengaluru, Karnataka. It serves as the principal research and development arm of the Department of Space (DoS), overseen by the Prime Minister of India, with the Chairman of ISRO also serving as the chief executive of the DoS. It is primarily responsible for space-based operations, space exploration, international space cooperation and the development of related technologies. The agency maintains a constellation of imaging, communications and remote sensing satellites. It operates the GAGAN and IRNSS satellite navigation systems. It has sent three missions to the Moon and one mission to Mars. Formerly known as the Indian National Committee for Space Research (INCOSPAR), ISRO was set up in 1962 by the Government of India on the recommendation of scientist Vikram Sarabhai. It was renamed as ISRO in 1969 and was subsumed into the Department of Atomic Energy (DAE). The establi ... [...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 and the second called . In the preburner, a small portion of propellant, usually fuel-rich, is partly combusted under non- stoichiometric conditions, increasing the volume of flow driving 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 flowin ... [...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 ... [...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 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 and the second called . In the preburner, a small portion of propellant, usually fuel-rich, is partly combusted under non- stoichiometric conditions, increasing the volume of flow driving 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 flowin ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
CE-20
The CE-20 is a cryogenic rocket engine developed by the Liquid Propulsion Systems Centre (LPSC), a subsidiary of the Indian Space Research Organisation (ISRO). It has been developed to power the upper stage of the LVM3. It is the first Indian cryogenic engine to feature a gas-generator cycle. The high thrust cryogenic engine is the most powerful upper stage cryogenic engine in operational service. Among the thrust levels for which CE-20 is qualified are 19 tonnes for ongoing satellite missions, 20 tonnes for the Gaganyaan, and an upgraded 22 tonnes for future launches like the Bharatiya Antariksha Station's BAS-01 Base Module. Overview The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle. The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between these limits. The combustion chamber burns liquid hydrogen and liquid oxygen at 6 MPa with ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Geostationary Transfer Orbit
In space mission design, a geostationary transfer orbit (GTO) or geosynchronous transfer orbit is a highly elliptical type of geocentric orbit, usually with a perigee as low as low Earth orbit (LEO) and an apogee as high as geostationary orbit (GEO). Satellites that are destined for geosynchronous orbit (GSO) or GEO are often put into a GTO as an intermediate step for reaching their final orbit. 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. Manufacturers of launch vehicles often advertise the amount of payload the vehicle can put into GTO. Background Geostationary and geosynchronous orbits are very desirable for many communication and Earth observation satellites. However, the delta-v, and therefore financial, cost to send a spacecraft to such orbits is very high due to their high orbital radius. A GTO is an intermedia ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
India
India, officially the Republic of India, is a country in South Asia. It is the List of countries and dependencies by area, seventh-largest country by area; the List of countries by population (United Nations), most populous country since 2023; and, since its independence in 1947, the world's most populous democracy. 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 near 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 averag ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
