Encyclopedia Astronautica Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z Encyclopedia Astronautica Index: 2 2.4KS5600 - Alternate designation for Hopi 2.4KS5600 Solid rocket engine. 2.5KS18000 - Multiple-source solid rocket engine. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s. Status: Retired 1985. Gross mass: 272 kg (599 lb). Unfuelled mass: 153 kg (337 lb). Thrust: 80.00 kN (17,984 lbf). Propellants: Solid. 2.67-KS-459 - Alternate designation for Star 5C Solid rocket engine. 2.80-KS-439 - Alternate designation for Star 5C/CB Solid rocket engine. 20.20 comsat - American communications satellite. Design of 2008, provided greater digital communications capacity by integrating next-generation technologies with the proven reliability of traditional concepts and products of the FS 1300 series. Status: Design 2008. Gross mass: 8,500 kg (18,700 lb). 200 inch solid engine series - 200 inch solid segment x 4 - Notional solid rocket engine. Study 1960. 4 used as first stage of NASA all-solid Nova design. Extended high-expansion nozzles. Solid propellant rocket stage. Conceptual motor to be used as first stage of a solid Nova design. 4 used as first stage of solid Nova design. Extended high-expansion nozzles. Masses estimated based on total vehicle thrust, performance, and stage volumes. Status: Study 1960. Thrust: 11,120.00 kN (2,499,870 lbf). Propellants: Solid. 200 inch solid segment x 6 - Notional solid rocket engine. NASA Nova study 1960. 5 used as first stage of solid Nova design. Solid propellant rocket stage. 5 used as first stage of solid Nova design. Masses estimated based on total vehicle thrust, performance, and stage volumes. Status: Study 1960. Thrust: 28,017.00 kN (6,298,472 lbf). Propellants: Solid. 205 - Alternate designation for Tu-121. 205 missile - Russian surface-to-air missile. Original missile of the S-25 system, development described above. 206 missile - Russian surface-to-air missile. The 206 was a version of the 205 using a single-chamber Isayev engine in place of the four-chamber design of the 205. Cancelled in April 1953. 207 missile - Russian surface-to-air missile. This was an improvement of the 205 with an improved warhead and reduced cruise thrust. Trials were conducted of the missile in 1953, but it was decided not to put it into service. Thrust: 88.20 kN (19,828 lbf). 207A - Russian surface-to-air missile. The 207A, with numerous improvements to the 205 which had been developed in a crash program, completed trials in 1955 and rapidly replaced the 205 in PVO service. It basically doubled all of the performance characteristics of the 205. 207T - Russian surface-to-air missile. The 207T was an alternative derivative of the 207A with a nuclear warhead. It was developed during 1958 but does not seem to have entered service. 208 missile - Russian surface-to-air missile. In this version of the V-300 the warhead was increased to 430 kg to compensate for accuracy problems in the original production version. Cancelled in favor of the 207A. 210 missile series - Series of antiaircraft missiles designed by Korolev prior to his arrest in 1939. Abandoned thereafter. 212 missile - Russian air-to-surface missile. Korolev's second design for a rocket-propelled cruise missile. It was flight tested twice after his arrest in 1939 but work was then abandoned. Status: Cancelled 1940. Gross mass: 165 kg (363 lb). Thrust: 667 N (149 lbf). 215 missile - Russian surface-to-air missile. The 215 was a derivative of the 207A with a nuclear warhead. It entered service in 1957. 217 missile - Russian surface-to-air missile. The 217 was a version of the V-300 with a variable thrust engine. Entered production. Thrust: 166.00 kN (37,318 lbf). 217/I - First anti-aircraft missile flown in the USSR. The 217/I had a conventional aircraft layout, with a main wing and aerodynamic control surfaces on the tail. Gross mass: 120 kg (260 lb). Thrust: 18.14 kN (4,078 lbf). 217/II - Pre-World War II anti-aircraft missile flown in the USSR. The 217/II follow-on to the 217/I had the first 'rocket' layout - four small wings, each all-moving. Gross mass: 140 kg (308 lb). 217M - Russian surface-to-air missile. Developed together with the improved S-25M missile system, the 217M entered production and gave the S-25 an enormous performance in improvement. 218 missile - Russian surface-to-air missile. The 218 was a version of the 217M with a nuclear warhead, which entered service in 1964. 21AL-2600 - Aerojet Nitric acid/Amine rocket engine. Development begun January 1946. Regeneratively cooled. Development and production First flight 1953. Date: January 1946. Thrust: 11.70 kN (2,630 lbf). Propellants: Nitric acid/Amine. 21KS - Manufacturer's designation for SPK space suit. 22.6KS1245 - Multiple-source American solid rocket engine. Sparoair III second stage. Status: Retired 1966. Gross mass: 100 kg (220 lb). Thrust: 5.50 kN (1,236 lbf). Propellants: Solid. 22D - Russian surface-to-air missile. Prototype surface-to-air missile, using liquid-propellant ramjets in place of the air-augmented solid propellant of the 17D. Status: Cancelled 1958. 23KS11000 - Aerojet solid rocket engine. Status: Retired 1974. Gross mass: 500 kg (1,100 lb). Unfuelled mass: 200 kg (440 lb). Thrust: 49.00 kN (11,015 lbf). Propellants: Solid. 23KS20000 - Bristol Aerospace solid rocket engine. Two-finned version. Bristol Aerospace solid rocket engine. Two-finned version. Status: Retired 1965. Gross mass: 1,000 kg (2,200 lb). Unfuelled mass: 150 kg (330 lb). Thrust: 89.00 kN (20,007 lbf). Propellants: Solid. 240 inch solid - Solid propellant rocket stage. Notional 240 inch solid motor considered in cluster of 4 as alternative to Nova 8 F-1 stage. Led to 260 inch motor tested in late 1960's. Status: Study 1960. Gross mass: 1,633,000 kg (3,600,000 lb). Unfuelled mass: 163,000 kg (359,000 lb). Thrust: 24,457.00 kN (5,498,152 lbf). Propellants: Solid. 25AL-1000 - Aerojet Nitric acid/Amine rocket engine for A-20 ATO. Development begun May 1942. Production version of GALCIT unit. First flight 1944. Date: May 1942. Unfuelled mass: 109 kg (240 lb). Thrust: 4.41 kN (991 lbf). Propellants: Nitric acid/Amine. 25XALD-1000 - Aerojet Nitric acid/Amine JATO rocket engine. Development begun May 1942. Droppable version of XLR1, packaged compactly with parachute, for P-38, B-24, and B-25J. First flight 1944. Date: May 1942. Unfuelled mass: 124 kg (273 lb). Thrust: 4.41 kN (991 lbf). Propellants: Nitric acid/Amine. 260 inch solid FL - Alternate name for AJ-260X. 260 inch solid HL - Alternate name for AJ-260-2. 260 inch solid TL - Alternate name for AJ-260-1/3. 26KS20000 - Bristol Aerospace solid rocket engine. Four-finned version. Solid propellant rocket stage. Four-finned version. Status: Active. Number: 578 . Gross mass: 1,264 kg (2,786 lb). Unfuelled mass: 268 kg (590 lb). Thrust: 75.70 kN (17,018 lbf). Propellants: Solid. 27.5-KS-6,100 - Alternate designation for Altair 3 Solid rocket engine. 27KS - Manufacturer's designation for Mir complex manned space station. 280 inch solid - Notional solid rocket engine. Study 1963. Operational date would have been February 1973 Used on Nova MM 14B launch vehicle. Solid propellant rocket stage. Operational date would have been February 1973. Nova MM 14B first stage. Status: Study 1963. Thrust: 46,208.00 kN (10,387,971 lbf). Propellants: Solid. 28-KS-4,825 - Alternate designation for Star 24C Solid rocket engine. 29.6-KS-4,170 - Alternate designation for Star 24 Solid rocket engine. 293-P - Kartukov solid rocket engine. P-70 Ametist. Out of Production. Status: Out of Production. Date: 1959-68. Propellants: Solid. 2D - Alternate designation for Elektron-A. 2K - Manufacturer's designation for Zenit-2 satellite military surveillance satellite. 2K11 - Article number for Krug. 2K12 - Article number for Kub. 2K6 - Article number for 3R9. 2K6 - Article number for 3R10. 2K6 - Article number for Frog 5. 2KM - Manufacturer's designation for Zenit-2M satellite military surveillance satellite. 2MS - Russian technology satellite. Early Kosmos launcher payloads of unknown purpose, possibly from Korolev OKB. Status: Operational 1962. First Launch: 1962-04-24. Last Launch: 1962-05-28. Number: 2 . Gross mass: 305 kg (672 lb). 2MV - Spacecraft bus designed by Korolev 1960 for Mars and Venus flyby missions. Handed over to Lavochkin for further development in mid-1960's. 2MV - Alternate designation for Mars 2MV-1. 2MV-1 - Manufacturer's designation for Mars 2MV-1 Venus probe. 2MV-2 - Manufacturer's designation for Mars 2MV-2 Venus probe. 2MV-3 - Manufacturer's designation for Mars 2MV-3 Venus probe. 2MV-4 - Manufacturer's designation for Mars 2MV-4 mars flyby probe. 2V - Alternate designation for Venera 2V (V-69). 2V (V-69) - Manufacturer's designation for Venera 2V (V-69) Venus probe. Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z © 1997-2016 Mark Wade - Contact © / Conditions for Use |
