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Spacecraft propulsion is any method used to accelerate spacecraft and artificial satellites. In-space propulsion exclusively deals with propulsion systems used in the vacuum of space and should not be confused with space launch or atmospheric entry.
An ion thruster, ion drive, or ion engine is a form of electric propulsion used for spacecraft propulsion. It creates thrust by accelerating ions using electricity.
Specific impulse is a measure of how efficiently a reaction mass engine creates thrust. For engines whose reaction mass is only the fuel they carry, specific impulse is exactly proportional to the effective exhaust gas velocity.
Kosmos 21 was a Soviet spacecraft. This mission has been tentatively identified by NASA as a technology test of the Venera series space probes. It may have been an attempted Venus impact, presumably similar to the later Kosmos 27 mission, or it may have been intended from the beginning to remain in geocentric orbit. In any case, the spacecraft never left Earth orbit after insertion by the Molniya launcher. The orbit decayed on 14 November 1963, three days after launch.
Aleksei Mikhailovich Isaev was a Russian rocket engineer.
Spacecraft electric propulsion is a type of spacecraft propulsion technique that uses electrostatic or electromagnetic fields to accelerate mass to high speed and thus generate thrust to modify the velocity of a spacecraft in orbit. The propulsion system is controlled by power electronics.
The Keldysh bomber was a Soviet design for a rocket-powered sub-orbital bomber spaceplane, which drew heavily upon work carried out by Eugen Sänger and Irene Bredt for the German Silbervogel project.
Waxwing was a British solid rocket motor used for apogee kick as the 3rd (upper) stage of the Black Arrow satellite launch vehicles. Waxwing was used to successfully place the Prospero X-3 satellite into low Earth orbit on 28 October 1971, Britain's only satellite launch on an indigenously developed launch vehicle.
A black powder rocket motor propels a model rocket using black powder. Black powder rocket propellants consist of charcoal, sulfur, and potassium nitrate. Adjustments can be made to the amount of each component to change the rate at which the black powder burns.
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 S5.92 is a Russian rocket engine, currently used on the Fregat upper stage.
The KTDU-35 was a Soviet spacecraft propulsion system composed of two liquid rocket engines, the primary, S5.60 (SKD) and the secondary S5.35 (DKD), fed from the same propellant tanks. Both engines burn UDMH and AK27I in the gas generator cycle. It was designed by OKB-2, the famous Isaev Design Bureau, for the original Soyuz programme.
The KTDU-80 (Russian: Корректирующе-Тормозная Двигательная Установка, КТДУ) is the latest of a family of integrated propulsion system that KB KhIMMASH has implemented for the Soyuz since the Soyuz-T. It integrates main propulsion, RCS and attitude control in a single system pressure fed from a common dual string redundant pressurized propellant system. The common propellant is UDMH and N2O4 and the main propulsion unit, is the S5.80 main engine. It generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 880 kPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The integrated system without the pressurization or tanks weighs 310 kg (680 lb); it is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).
The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module. The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).
The A.M. Isayev Chemical Engineering Design Bureau, also known as KB KhimMash or just KBKhM, is a Russian rocket engine design and manufacturing company. It is located in the city of Korolyov. It started as the OKB-2 division of the NII-88 research institute, where A.Isaev directed the development of liquid rocket engines for ballistic missile submarines.
The S5.142 (AKA DST-25) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It was used in KTDU-80 propulsion module from the Soyuz-TM to the Soyuz-TMA-M, as the low thrust thruster (DPO-M). As of the Soyuz MS, KTDU-80 does not use DPO-M anymore.
The 4MV planetary probe is a designation for a common design used for Soviet unmanned probes to Mars and Venus. It was an incremental improvement of earlier 3MV probes and was used for Mars missions 2 to 7 and Venera missions 9 to 16. The same base design was used for some earth-orbiting space observatories.
The 1MV planetary probe is a designation for a common design used by early Soviet uncrewed probes to Mars and Venus. It was standard practice of the Soviet space program to use standardized components as much as possible. All probes shared the same general characteristics and differed only in equipment necessary for specific missions. Each probe also incorporated improvements based on experience with earlier missions. It was superseded by the 2MV family.
The Mars-69/M-69 or 2M was the designation given to 2 Soviet Mars probes that were to be sent in 1969. Based on the Luna E-8 landers used for Luna 15-24, they were the first attempted Mars and Interplanetary Orbiters. The probes however were both destroyed in separate launches in early 1969.
The KDU-414, is a pressure-fed liquid rocket Propulsion Unit developed and produced by the Isayev Design Bureau. From 1960 onward, it powered several unmanned Soviet Spacecraft, including the first series of Molniya satellites, several Kosmos satellites as well as the space probes Mars 1, Venera 1, Zond 2 and Zond 3, featured as a part of standartized spacecraft buses known as KAUR-2, 2MV and 3MV.
References
- 1 2 "KTDU-425". www.astronautix.com. Archived from the original on December 28, 2016. Retrieved 2022-04-17.
- 1 2 "KTDU-425A". www.astronautix.com. Archived from the original on August 19, 2016. Retrieved 2022-04-17.
- 1 2 "Spacecraft-propulsion blocks from Isayev Design bureau (Khimmash)". www.b14643.de. Retrieved 2022-04-17.