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Energia was a 1980s super-heavy lift launch vehicle. It was designed by NPO Energia of the Soviet Union as part of the Buran programme for a variety of payloads including the Buran spacecraft. Control system main developer enterprise was the Khartron NPO "Electropribor". The Energia used four strap-on boosters each powered by a four-chamber RD-170 engine burning kerosene/LOX, and a central core stage with four single-chamber RD-0120 (11D122) engines fueled by liquid hydrogen/LOX.
Soyuz is a family of expendable Russian and Soviet carrier rockets developed by OKB-1 and manufactured by Progress Rocket Space Centre in Samara, Russia. With over 1,900 flights since its debut in 1966, the Soyuz is the most frequently used launch vehicle in the world as of 2021.
Pivdenne Design Office (Ukrainian: Державне конструкторське бюро «Південне» ім. М. К. Янгеля, romanized: Derzhavne konstruktorske biuro "Pivdenne" im. M. K. Ianhelia, lit. 'State design bureau "Southern", named after M. K. Yangel'; located in Dnipro, Ukraine, is a designer of satellites and rockets, and formerly of Soviet intercontinental ballistic missiles established by Mikhail Yangel. During Soviet times the bureau's OKB designation was OKB-586.
Zenit is a family of space launch vehicles designed by the Yuzhnoye Design Bureau in Dnipro, Ukraine, which was then part of the Soviet Union. Zenit was originally built in the 1980s for two purposes: as a liquid rocket booster for the Energia rocket and, equipped with a second stage, as a stand-alone middle-weight launcher with a payload greater than the 7 tonnes of the Soyuz but smaller than the 20 tonnes payload of the Proton. The last rocket family developed in the USSR, the Zenit was intended as an eventual replacement for the dated Soyuz and Proton families, and it would employ propellants which were safer and less toxic than the Proton's nitrogen tetroxide/UDMH mix. Zenit was planned to take over crewed spaceship launches from Soyuz, but these plans were abandoned after the dissolution of the Soviet Union in 1991.
The Angara rocket family is a family of launch vehicles being developed by the Moscow-based Khrunichev State Research and Production Space Center. The launch vehicles are to put between 3,800 kg (8,400 lb) and 24,500 kg (54,000 lb) into low Earth orbit and are intended, along with Soyuz-2 variants, to replace several existing launch vehicles.
The RD-180 is a rocket engine designed and built in Russia. It features a dual combustion chamber, dual-nozzle design and is fueled by a RP-1/LOX mixture. The RD-180 is derived from the RD-170/RD-171 line of rocket engines, which were used in the Soviet Energia launch vehicle and are still in use in the Ukrainian Zenit launch vehicles.
The NK-33 and NK-43 are rocket engines designed and built in the late 1960s and early 1970s by the Kuznetsov Design Bureau. The NK designation is derived from the initials of chief designer Nikolay Kuznetsov. The NK-33 was among the most powerful LOX/RP-1 rocket engines when it was built, with a high specific impulse and low structural mass. They were intended for the ill-fated Soviet N1F moon rocket, which was an upgraded version of the N1. The NK-33A rocket engine is now used on the first stage of the Soyuz-2-1v launch vehicle. When the supply of the NK-33 engines are exhausted, Russia will supply the new RD-193 rocket engine. It used to be the first stage engines of the Antares 100 rocket series, although those engines are rebranded the AJ-26 and the newer Antares 200 and Antares 200+ rocket series uses the RD-181 for the first stage engines, which is a modified RD-191, but shares some properties like a single combustion chamber unlike the two combustion chambers used in the RD-180 of the Atlas V and the four combustion chambers used in the RD-170 of the Energia and Zenit rocket families, and the RD-107, RD-108, RD-117, and RD-118 rocket engines used on all of the variants of the Soyuz rocket.
The RD-8 is a Soviet / Ukrainian liquid propellant rocket engine burning LOX and RG-1 in an oxidizer rich staged combustion cycle. It has a four combustion chambers that provide thrust vector control by gimbaling each of the nozzles in a single axis ±33°. It was designed in Dnipropetrovsk by the Yuzhnoye Design Bureau as the vernier thruster of the Zenit second stage. As such, it has always been paired with the RD-120 engine for main propulsion.
The Geosynchronous Satellite Launch Vehicle Mark III, also referred to as the Launch Vehicle Mark 3 (LVM3), 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 identified as the launch vehicle for crewed missions under the Indian Human Spaceflight Programme and dedicated science missions like Chandrayaan-2. The GSLV Mk III has a higher payload capacity than the similarly named GSLV Mk II.
The Saturn II was a series of American expendable launch vehicles, studied by North American Aviation under NASA contract in 1966, derived from the Saturn V rocket used for the Apollo lunar program. The intent of the study was to eliminate production of the Saturn IB, and create a lower-cost heavy launch vehicle based on Saturn V hardware. North American studied three versions with the S-IC first stage removed: the INT-17, a two-stage vehicle with a low Earth orbit payload capability of 47,000 pounds (21,000 kg); the INT-18, which added Titan UA1204 or UA1207 strap-on solid rocket boosters, with payloads ranging from 47,000 pounds (21,000 kg) to 146,400 pounds (66,400 kg); and the INT-19, using solid boosters derived from the Minuteman missile first stage.
Atlas is a family of US missiles and space launch vehicles that originated with the SM-65 Atlas. The Atlas intercontinental ballistic missile (ICBM) program was initiated in the late 1950s under the Convair Division of General Dynamics. Atlas was a liquid propellant rocket burning RP-1 fuel with liquid oxygen in three engines configured in an unusual "stage-and-a-half" or "parallel staging" design: two outboard booster engines were jettisoned along with supporting structures during ascent, while the center sustainer engine, propellant tanks and other structural elements remained connected through propellant depletion and engine shutdown.
The Long March 6 or Chang Zheng 6 as in pinyin, abbreviated LM 6 for export or CZ 6 within China, is a Chinese liquid-fuelled launch vehicle of the Long March family, which was developed by the China Aerospace Science and Technology Corporation (CASC) and the Shanghai Academy of Spaceflight Technology (SAST). The rocket was developed in the 2000s, and made its maiden flight in 2015. As one of the new generation rocket family, the Long March 6 was designed to be a light capacity, "high-speed response" rocket, complementing the heavy lift Long March 5 and the mid-heavy lift Long March 7 rocket families. It is capable of placing at least 1,000 kg (2,200 lb) of payload into a Sun-synchronous orbit. The first stage of the Long March 6 was derived from the booster rockets being developed for the Long March 5 rocket. It is powered by a YF-100 engine, which generates 1,340 kN (300,000 lbf) of thrust from burning kerosene and LOX as rocket fuel and oxidiser. This was the first flight of the new engine design.
The RD-120 is a liquid upper stage rocket engine burning RG-1 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.
KVD-1 was an upper stage LOX/LH2 cryogenic engine developed by the Isayev Design Bureau (now KB KhIMMASH) of Russia in the early 1960s. It is a modified version of the RD-56, developed for a never-completed cryogenic upper stage of the N-1 super-heavy lift rocket, with the goal of enabling crewed lunar missions by the USSR. The KVD-1 produces a thrust of 7.5 tonnes.
The SCE-200 is an Indian, under-development, liquid-fuel rocket engine, burning liquid oxygen (LOX) and RP-1 kerosene in an oxidizer-rich staged combustion cycle. This engine is expected to power Indian Space Research Organization's upcoming Unified Launch Vehicle (ULV) and Reusable Launch Vehicle (RLV). It is being developed by the Liquid Propulsion Systems Centre, a subsidiary of ISRO. But before that it will be tested on a GSLV Mk III by replacing the L110 stage powered by the Vikas engine with an SC-200 stage powered by SCE-200 engine and a 200 tonne propellant load.
Liquid Fly-back Booster (LFBB) was a German Aerospace Center's (DLR's) project concept to develop a liquid rocket booster capable of reusing for Ariane 5 in order to significantly reduce the high cost of space transportation and increase environmental friendliness. LFBB would replace the existing solid rocket boosters, providing main thrust during the liftoff. Once separated, two winged boosters would perform an atmospheric entry, fly back autonomously to the French Guiana, and land horizontally on the airport like an aeroplane.
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 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.
A super heavy-lift launch vehicle can lift to low Earth orbit more than 50 metric tons (110,000 lb) by United States (NASA) classification or 100 metric tons (220,000 lb) by Russian classification. It is the most capable launch vehicle classification by mass to orbit, succeeding the heavy-lift launch vehicle classification. Crewed lunar and interplanetary missions are often developed around these launch vehicles' payload capacity.
The RD-801 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 +/- 6°. It is being designed in Ukraine by Yuzhnoye Design Bureau for the prospective first stage propulsion of the Mayak rocket family.
References
- ↑ "Mayak". State Space Agency of Ukraine. Retrieved 7 November 2015.
- 1 2 "Launch vehicles / Missiles / Mayak". Design Office . Retrieved May 25, 2016.
 Ukrainian launch vehicles | ||
|---|---|---|
| Cyclone (Tsyklon) |  | |
| Zenit | ||
| Mayak | ||
| Dnipro (Dnepr) | ||
| International projects | ||
