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U.S. Army Space & Missile Defense Center, USA
American agency.
Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 stage 2. Out of production. Isp=307s.
Isayev rocket engine. 12.7 kN. Developed 1945-46. Isp=208s.
Isayev rocket engine. 19.6 kN. for SAM. Out of Production.
Isayev rocket engine. 3.920 kN. Samolet 5. Developed 1946-47.
Russian manned rocketplane. Study 1949. Unmanned rocketplane that proved Isayev rocket engine technology in the late 1940's.
Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production.
Solid propellant rocket stage. Loaded/empty mass 544,311/37,195 kg. Thrust 8,924.48 kN. Vacuum specific impulse 263 seconds.
Solid propellant rocket stage. Loaded/empty mass 725,500/49,250 kg. Thrust 18,181.00 kN. Vacuum specific impulse 263 seconds. 4 Segment version of basic 3-segment UA 156 motor.
CSD solid rocket engine family.
CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strap-on boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965.
CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982.
CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989.
CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U.
UAE.
UAE
UARS.
American earth ionosphere satellite. One launch, 1991.09.12. The Upper Atmospheric Research Satellite was designed to study the physical and chemical processes occurring in the Earth's upper atmosphere (between 15 and 100 km).
UBM.
Unpressurized Berthing Mechanism
UCD.
Urine Containment Device - for men, a latex condom leading to a bladder than allowed them to void themselves during the sometimes-long wait on the pad for launch. For women, a Depends-type disposable diaper. Just not the wait, but the position of the astronauts, laying on their back with their legs up, brought on the urge, as demonstrated on Alan Shepherd's UCD-less first American flight into space.
Uchinoura.
Alternate name for Kagoshima launch site.
Uchinoura LCK
UC-L.
UC-L.
Udarov, Grigori Rafailovich (1904-1991) Russian government official. Deputy Minister of General Machine Building 1965-1979. Responsible for ground complexes.
UDMH.
Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance.
UFO.
Unidentified Flying Object
UGC.
Uppsala General Catalog
UGM-133A.
Department of Defence Designation of Trident D-5 intercontinental ballistic missile.
UGM-27A.
Department of Defence Designation of Polaris A1 missile.
UGM-27B.
Department of Defence Designation of Polaris A2 missile.
UGM-27C.
Department of Defence Designation of Polaris A3 missile.
UGM-73A.
Department of Defence Designation of Poseidon submarine-launched ballistic missile.
UGM-96A.
Department of Defence Designation of Trident C-4 intercontinental ballistic missile.
UGM-96B.
Alternate Designation of Trident D-5 intercontinental ballistic missile.
UH.
UH.
UHF.
Ultra High Frequency
UHF.
US Navy communications satellite network; Ultra High Frequency Follow On.
UIT.
Ultraviolet Imaging Telescope (Astro package)
UK.
United Kingdom(UK-X4).
UK.
UK
British agency. UK Defence Reseach Agency, UK.
Base for units deployed with R-12 missile.
Ukraine
Ukraine AF.
Requirement: pilots from Ukraine to visit Mir space station for propaganda purposes on Soyuz ferry-exchange mission.
UKST.
United Kingdom Schmidt Telescope
Directorate for Command of the Military Space Forces (Russian abbreviation)
Ulmer, Ralph E (1917-1985) American engineer, at NASA 1938-1973, budget officer and program analyst.
ULO.
Unmanned Launch Operations
Ultraviolet astronomy satellite.
Category of spacecraft.
European solar satellite. One launch, 1990.10.06. Ulysses was a joint NASA / ESA mission designed to study the polar regions of the Sun.
UM.
American manufacturer of rocket engines. UM, USA.
Nissan solid rocket engine. 77.5 kN. In Production. Used in H-1-3. Isp=291s.
Solid propellant rocket stage. Loaded/empty mass 2,200/360 kg. Thrust 77.40 kN. Vacuum specific impulse 291 seconds.
Soviet manned spacecraft. Study 1965. Small minimum space capsule for emergency return of crew or urgent payloads from orbit. Proposed by an engineer at Soviet Factory 918 in 1965, but no support from the entrenched space interests.
Univeristy of Michigan
American manufacturer of rocket engines. UM-JPL, USA.
Umm Qasr
American manufacturer of rocket engines. UM-NASA, USA.
Umpfenbach, Joachim (1902-) German propulsion expert. Member of German Rocket Team in the Soviet Union after WW2. One of the group that fired V-2 rockets at Kapustin Yar in 1946.
American manned Mars expedition. Study 1964. Unfavorable Manned Planetary - Interplanetary Roundtrip Expedition profiles were studied under NASA Huntsville contracts to General Dynamics and Douglas in June 1963.
American manned Mars expedition. Study 1964. Unfavorable Manned Planetary - Interplanetary Roundtrip Expedition profiles were studied under NASA Huntsville contracts to General Dynamics and Douglas in June 1963.
American manufacturer of rocket engines. UM-USAF, USA.
UN.
United Nations
UNAM.
Mexican agency. Autonomous University of Mexico, Mexico City, Mexico.
Italian technology satellite. 3 launches, 2000.09.26 (UniSat) to 2004.06.29 (Unisat 3). Experimental satellite developed by the GAUSS (Gruppo di Astrodinamica dell' Universita degli Studi 'la Sapienza') in Roma.
Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Launched 2010.05.20,
American manufacturer of spacecraft. United Aircraft, USA.
American manufacturer. United Technologies, USA.
United Technologies Corporation.
First Owner of CSD
American manufacturer of rocket engines. United Technology Center, USA.
Ukrainian intercontinental ballistic missile. Yuzhnoye solid-propellant ICBM designed for mass production to counter US 'Star Wars' programme. Two built before break-up of Soviet Union. Some design features incorporated into all-Russian Topol-M.
Universidad Politecnia de Madrid.
Spanish manufacturer of spacecraft. Universidad Politecnia de Madrid, Spain.
Russian technology satellite. One launch, 2005.01.20. Student satellite for radiation studies, ejected from Cosmos 2414.
Swiss manufacturer. University of Bern, Switzerland.
German manufacturer of spacecraft. University of Bremen, Germany.
UC.
University of Harbin.
First Owner of Harbin
British manufacturer of spacecraft. University of Surrey, UK.
UNKS.
Russian agency. Directorate of the Commander of Space Assets, Russia.
Unmanned Logistic System.
Alternate designation for Apollo ULS lunar logistics spacecraft.
Brazilian technology satellite.
UNRV.
Directorate of the Commander of Reactive Armaments (Russian abbreviation)
British amateur radio communications satellite. One launch, 2001.09.30, Picosat. Radio science; also carried amateur radio package. Communication and geophysics research satellite.
UP Aerospace.
American manufacturer of rockets. Up Industries, USA.
Upgraded Solid Rocket Motor.
Alternate designation for Titan USRM rocket stage.
Upham.
Alternate name for Spaceport America launch site.
UPI.
United Press International
UPM.
Spanish manufacturer of spacecraft. Madrid Polytechnic University, Madrid, Spain.
UPMK.
Cosmonaut Manoeuvring and Motion Unit (Russian abbreviation)
Upper Atmosphere Research Satellite.
Alternate designation for UARS earth ionosphere satellite.
Category of engines.
American orbital launch vehicle. Initial version of Saturn IB with old-design Saturn IB first stage.
American sounding rocket. Sprint test vehicle.
Boeing solid rocket engine.
Solid propellant rocket stage. Loaded mass 6,000 kg.
UQU.
Australian agency. University of Queensland, Queensland, Australia.
UR-.
Universal Rocket (designation numbering series) (Russian abbreviation)
The UR-100 lightweight ICBM was the Soviet answer to the US Minuteman and was deployed in larger numbers than any other in history. It remained an enigma outside of intelligence circles in the West until after the collapse of the Soviet Union. It allowed the Soviet Union to match, and then surpass the United States in strategic deterrent capability. As such it was Vladimir Chelomei's crowning legacy to his country.
Russian intercontinental ballistic missile. The UR-100 lightweight ICBM was the Soviet answer to the US Minuteman and was deployed in larger numbers than any other in history. It remained an enigma outside of intelligence circles in the West until after the collapse of the Soviet Union. It allowed the Soviet Union to match, and then surpass the United States in strategic deterrent capability. As such it was Vladimir Chelomei's crowning legacy to his country.
Russian intercontinental ballistic missile. The UR-100K was a version of the 8K84M with further improvements in accuracy and capable of delivering three separate (but not independently targeted) re-entry vehicles.
Russian intercontinental ballistic missile. The 8K84M was an improved version of the UR-100 with an improved empty mass fraction, a new guidance system, countermeasures capability, and post-boost manoeuvrability to defeat enemy anti-ballistic missile systems.
Russian intercontinental ballistic missile. The UR-100M designation was used for a naval version of the UR-100, developed by Chelomei in 1962-1964. This would fit in the Navy's D-8 launch system. It was rejected in favour of the R-29 from Makeyev, who became the Navy's traditional supplier of SLBM's.
Russian intercontinental ballistic missile. The UR-100N was designed as a replacement for the UR-100 at the end of its ten year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Yangel, the MR-UR-100, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other.
The UR-100N was designed as a replacement for the UR-100 at the end of its ten year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Yangel, the MR-UR-100, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,100/725 kg. Thrust 4.90 kN. Vacuum specific impulse 200 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 77,150/5,695 kg. Thrust 1,778.66 kN. Vacuum specific impulse 310 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 12,195/1,485 kg. Thrust 214.27 kN. Vacuum specific impulse 322 seconds. Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff.
Russian intercontinental ballistic missile. Development of an improved version of the UR-100N was authorised on 16 April 1976 (UR-100NU; U = UTTKh = 'Improved Technical-Tactical Characteristics). Viktor Bugaisk at TsKBM headed the engineering team. The UR-100NU was to have a new warhead dispenser bus and improved guidance system by Vladimir Sergeyev of NII-692. The new system allowed up to six pre-programmed targets to be entered, any one of which could be selected at launch. This allowed deployment of better countermeasures and a considerable improvement in accuracy.
UR-100NU 15A35.
Alternate designation for UR-100NU intercontinental ballistic missile.
Russian intercontinental ballistic missile.
Russian intercontinental ballistic missile.
UR-100NUTTKh.
Alternate Designation of UR-100NU intercontinental ballistic missile.
Russian intercontinental ballistic missile. The UR-100U was a development of the UR-100K with improved shock isolation in the silo.
Russian intercontinental ballistic missile. Universal rocket designed by Chelomei to cover the ICBM, FOBS, satellite launch vehicle, and spaceplane booster roles. Flight tested in 1963-1964 but cancelled in favour of Yangel's R-36.
Universal rocket designed by Chelomei to cover the ICBM, FOBS, satellite launch vehicle, and spaceplane booster roles. Flight tested in 1963-1964 but cancelled in favour of Yangel's R-36.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 107,500/6,600 kg. Thrust 2,235.00 kN. Vacuum specific impulse 311 seconds. Tsniimash has 1:10 structural simulation model. Developed 1960-1965. Orevo has sectioned hardware. All data accurate except empty mass prorated between first and second stages.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 25,810/2,400 kg. Thrust 612.90 kN. Vacuum specific impulse 322 seconds. Tsniimash has 1:10 structural simulation model. Developed 1960-1965. Orevo has sectioned hardware. All data accurate except empty mass prorated between first and second stages.
Russian intercontinental boost-glide missile. Version that would boost the Raketoplan combat re-entry vehicle, which would use aerodynamic horizontal and vertical manoeuvring to penetrate enemy space defences and be practically invulnerable.
Russian orbital missile. Global rocket version. Would place nuclear warhead into orbit, which would approach United States from any direction at low altitude and be deorbited with little warning time on on enemy targets.
UR-500.
Manufacturer's designation for Initial UR-500, Monoblock UR-500, and Polyblock UR-500 orbital launch vehicles.
Russian orbital launch vehicle. The original UR-500 two stage configuration was designed as a monster ICBM. It was flown four times from 1965, but never deployed as an operational missile. The design was succeeded by three and four stage versions for launching of large payloads into space.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 367,360/25,560 kg. Thrust 8,989.70 kN. Vacuum specific impulse 310 seconds. Original conventional 'Monoblock' design for Proton first stage.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 378,900/26,900 kg. Thrust 8,989.70 kN. Vacuum specific impulse 310 seconds. Original 'Polyblock' design for Proton first stage. This was selected configuration; although somewhat greater in dry mass, it had the advantages of shorter length.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 137,700/16,000 kg. Thrust 3,183.20 kN. Vacuum specific impulse 320 seconds. Original Proton second stage design.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 23,940/2,180 kg. Thrust 613.11 kN. Vacuum specific impulse 320 seconds. Original Proton third stage design.
UR-500K.
Manufacturer's designation for Proton-K orbital launch vehicle.
UR-500KM.
Manufacturer's designation for Proton-K-Briz-M orbital launch vehicle.
Russian orbital launch vehicle. In 1975 Chelomei proposed this version of the Proton powered by lox/kerosene NK-33 engines developed for the cancelled N1 moon booster. This would give the Soviet Union an equivalent to the all-new Zenit-2 booster being developed by Glushko, but at a fraction of the time and expense through the use of existing components. The proposal had no chance politically, and was never seriously considered.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 137,000/9,300 kg. Thrust 1,637.00 kN. Vacuum specific impulse 331 seconds. Empty mass estimated based on overall vehicle mass fraction. Length estimated based on total mass.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 161,000/11,000 kg. Thrust 1,860.00 kN. Vacuum specific impulse 346 seconds. Empty mass estimated based on overall vehicle mass fraction. Length estimated based on total mass.
Russian orbital launch vehicle. Design for an upgraded Proton, replacing the first stage with a cluster of six modular stages derived from the UR-100N first stage. Detail design to the draft project stage was undertaken in 1976-1977 but the much larger and more expensive Energia/Buran system was selected for development instead.
Russian heavy-lift orbital launch vehicle. The UR-700 was the member of Vladimir Chelomei's Universal Rocket family designed in the 1960's to allow direct manned flight by the LK-700 spacecraft to the surface of the moon. However Korolev's N1 was the selected Soviet super-booster design. Only when the N1 ran into schedule problems in 1967 was work on the UR-700 resumed. The draft project foresaw first launch in May 1972. But no financing for full scale development was forthcoming; by then it was apparent that the moon race was lost.
The UR-700 was the member of Vladimir Chelomei's Universal Rocket family designed in the 1960's to allow direct manned flight by the LK-700 spacecraft to the surface of the moon. Later versions, some of completely different configuration, were studied for manned Mars expeditions.
Russian heavy-lift orbital launch vehicle. UR-700 with high energy upper stage consisting of 9 x RD-54 / 11D54 Lox/LH2 engines with a total thrust of 360 tonnes. Usable third stage propellant 300 tonnes, payload to a 200 km, 51.5 degree orbit increased to 185 tonnes
Russian heavy-lift orbital launch vehicle. UR-700 with high energy upper stage consisting of 3 x RD-350 LF2/LH2 engines with a total thrust of 450 tonnes. Usable third stage propellant 350 tonnes, payload increased to 215 tonnes
Russian heavy-lift orbital launch vehicle. UR-700 with high energy upper stage consisting of 7 x RO-31 Nuclear A engines using LH2+Methane propellants with a total thrust of 280 tonnes. Usable third stage propellant 196 tonnes, payload increased to 230 to 250 tonnes
N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,210,000/222,100 kg. Thrust 40,364.00 kN. Vacuum specific impulse 322 seconds. Includes propellant tanks which fed stage two engines from liftoff to first stage cutoff.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,072,000/75,600 kg. Thrust 20,182.00 kN. Vacuum specific impulse 322 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 399,400/26,000 kg. Thrust 5,139.60 kN. Vacuum specific impulse 328 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 33,500/1,900 kg. Thrust 131.40 kN. Vacuum specific impulse 326 seconds. Estimated empty mass. Three used to propell LK-700 spacecraft towards moon.
Russian heavy-lift orbital launch vehicle. In 1969 the Soviet Union began project Aelita, studying the best method to beat the Americans in landing a man on Mars. Chelomei's team reached the conclusion that a Mars expedition would best be launched by an immense vehicle would allow their MK-700 Mars spacecraft to be orbited in two launches. The proposed UR-700M launch vehicle had a gross lift-off mass of 16,000 metric tons and could deliver 750 metric tons to orbit. By 1972 the Nixon administration had cancelled NASA's plans for manned Mars missions. Perhaps not coincidentally, a Soviet expert commission the same year concluded that the Mars project - and the UR-700M booster - were beyond the technical and economical capabilities of the Soviet Union and should be shelved indefinitely.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,000,000/750,000 kg. Thrust 204,027.00 kN. Vacuum specific impulse 337 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on follow-on RD-170 engines.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 5,250,000/500,000 kg. Thrust 102,013.60 kN. Vacuum specific impulse 337 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on follow-on RD-170 engines.
Lox/LH2 propellant rocket stage. Loaded/empty mass 2,000,000/200,000 kg. Thrust 11,700.00 kN. Vacuum specific impulse 455 seconds. Total mass, length, estimated based on empty mass, total vehicle mass. Engine specific impulse estimated based on performance requirements.
Rocket stage used on UR-700 launch vehicle.
Russian heavy-lift orbital launch vehicle. In 1962 Vladimir Chelomei proposed a family of modular launch vehicles. In January 1969, Chelomei was proposing the UR-900 for the Mars expedition. A garbled description of this launch vehicle appears in Chertok's memoirs. This would seem to be a version of the UR-700 moon rocket using 15 RD-270 modules in the first and second stages in place as opposed to the nine modules of the UR-700. The third and fourth stages were derived from the UR-500. The booster could deliver 240 tonnes to low earth orbit.
Uragan.
Code name for Glonass navigation satellite.
Russian manned combat spacecraft. 2 launches, 1987.08.01 (Cosmos 1871) to 1987.08.28 (Cosmos 1873). Russian sources continue to maintain that the Uragan manned spaceplane project never existed.
Ural.
Popular Name of UR-500 missile.
Uran.
Code name for IS-P military anti-satellite system target satellite.
Urbani, Luca (1957-) Italian physician payload specialist astronaut, 1995-1996. Alternate Payload Specialist for STS-78 Mission LMS-1. Italian Air Force.
Urbanski, Arthur P (1900-1977) German-American engineer in WW2, member of the Rocket Team in the United States thereafter. As of 1960, Head of Mechanical Systems Analsysis Branch, Quality Division, NASA Marshall Space Flight Center. Died at Huntsville.
Urda.
Urda
Chinese mobile long range ballistic missile test area.
US.
Family of spacecraft.
US.
American agency.
American agency overseeing development of spacecraft. US Army, USA.
Category of launch vehicles.
Category of spacecraft.
Wernher von Braun brought Noordung's rotating station design with him from Europe. This he popularized in the early 1950's in selling manned space flight to the American public. By the late 1950's von Braun's team favoured the spent-stage concept - which eventually flew as Skylab. By the mid-1960's, NASA was concentrating on modular, purpose-built, zero-G stations. These eventually flew as the International Space Station.
USA.
USA
USA.
United States Army.
US-A.
Russian military naval surveillance radar satellite. 38 launches, 1965.12.28 (Cosmos 102) to 1988.03.14 (Cosmos 1932). The US-A (later known as RLS) was a nuclear powered RORSAT (Radar Ocean Reconnaissance Satellite).
American earth magnetosphere satellite. One launch, 2005.09.23. Classified research satellite, said to carry instruments to characterise the space environment in a sun-synchronous orbit.
American military technology satellite. One launch, 2006.12.14, US shoots down failed USA 193 satellite.. Classifed NRO mission of uncertain objectives, possibly military observation with a mixed payload.
American agency. Army Ballistic Missile Agency, USA.
American agency. USA ACE, USA.
American agency. US Army Ballistic Missiles Office, USA.
American agency. US Army Ballistic Research Laboratory, USA.
American agency. US Army Engineer Research and Development Laboratory, USA.
American agency. USA MDA, USA.
American agency. US Army Ordnance Research and Development Division Sub-Office (Rocket), USA.
American agency. US Army Signal Corps Engineering Laboratories, USA.
American agency. US Army Strategic Defense Command, USA.
American agency. US Army Space and Missile Defense Command, USA.
American agency. US Army Signal Research and Development Laboratory, USA.
American agency. US Army Space and Strategic Defense Command, USA.
American agency. USA TOPO, USA.
American agency. US Army 84th Field Artillery, USA.
Usachyov, Yuri Vladimirovich (1957-) Russian engineer cosmonaut. Flew on Mir EO-15, Mir EO-21, STS-101, ISS EO-2. 552 cumulative days in space.
USAF.
American agency overseeing development of rockets and spacecraft. United States Air Force, USA.
USAF Academy, Colorado Springs, USA
American agency. Air Combat Command, USA.
American agency. USAF AFC, USA.
American agency. Air Force Materiel Command, USA.
American agency. Air Force Systems Command, USA.
American agency. Air Force Space Command, USA.
American agency. Air Force Special Weapons Center, USA.
American agency. Air Proving Ground Command, USA.
American agency. USAF Ballistic Systems Division, USA.
American agency. Ballistic Missiles Office, USA.
American manufacturer of spacecraft. USAF Colorado Springs, Colorado Springs, Colorado, USA.
American agency. Air Force Cambridge Research Laboratories, USA.
Requirement: pilots for X-20A Dyna-Soar spaceplane flights.
Requirement: supplemental pilot for X-20A Dyna-Soar spaceplane flights to replace Armstrong and Dana.
American agency. Aerospace Research Pilot School.
American agency. Eastern Test Range, USA.
American agency. US Air Force Geophysics Laboratory, USA.
Requirement: crews for flights of the Manned Orbiting Laboratory, a classified military manned space station.
Requirement: crews for flights of the Manned Orbiting Laboratory, a classified military manned space station.
Requirement: crews for flights of the Manned Orbiting Laboratory, a classified military manned space station.
American agency. National Air Intelligence Center, USA.
American agency. USAF OAR, USA.
American manned space station. Study 1962. During 1962 NASA Centers, the Air Force, and many of the major aerospace contractors were developing possible space station concepts and studying their potential uses.
American agency. USAF Research Laboratory, USA.
American agency. USAF Rome, Rome, New York, USA.
American agency. Strategic Air Command, USA.
American agency overseeing development of spacecraft. Space and Missile Systems Organization, USA.
American agency overseeing development of spacecraft. Air Force Space and Missiles Command, USA.
American agency overseeing development of spacecraft. USAF SOR, USA.
American agency overseeing development of spacecraft. USAF STP, USA.
American agency. USAF Study, USA.
American agency. Tactical Air Command, USA.
American manufacturer. USAFA, USA.
US-AM.
Manufacturer's designation for US-A military naval surveillance radar satellite.
American manufacturer. USAMICOM, USA.
USB.
Universal Service Block (Russian abbreviations)
USB.
Russian military anti-satellite system. Study 1978. As platforms for operational versions of space-borne weapons NPO Energia designed a Universal Service Block, based on the DOS-7K space station, in the late 1970's/early 1980's.
USC.
American manufacturer. USC, USA.
USCG.
USCG.
US Coast Guard Cutter
USEF.
Japanese agency. USEF, Japan.
Japanese materials science satellite. One launch, 2002.09.10. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite.
USK.
Space system to observe rocket launches (Russian abbreviations)
US-KMO.
Manufacturer's designation for Prognoz SPRN military early warning satellite.
US-KS.
Manufacturer's designation for Oko military early warning satellite.
USM No. 176-01.
Manufacturer's designation for ISS Zvezda manned space station.
USMC.
USMC.
USMP.
United States Microgravity Payload
USN.
American agency overseeing development of rockets, spacecraft, and rocket engines. USN Joint Task Force 7, USA.
American agency. USN NASC, USA.
Naval Prop Plant.
American agency. Naval Missile Center, USA.
American agency. Naval Ordnance Laboratory, USA.
American agency. Naval Ordnance Test Station, USA.
American agency. Office of Naval Research, USA.
American agency. USN Postgraduate School, USA.
USNA.
American manufacturer of spacecraft. United States Naval Academy, USA.
US-P.
Russian military naval signals reconnaisance satellite. 37 launches, 1974.12.24 (Cosmos 699) to 1991.01.18 (Cosmos 2122). The US-P (later known as RTR) was a solar powered EORSAT (Electronic Ocean Reconnaissance Satellite).
US-PM.
Manufacturer's designation for US-P military naval signals reconnaisance satellite.
US-PU.
Manufacturer's designation for Pirs-2 military naval signals reconnaisance satellite.
Ukrainian military naval signals reconnaisance satellite. 13 launches, 1993.03.30 (Cosmos 2238) to 2006.06.24 (Cosmos 2421).
USRM.
Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strap-on booster for Titan 4B. First flight 1997.
USSR.
USSR
Ustinov, Dmitri Fedorovich (1908-1984) Russian politician. Primary manager of the Soviet missile and space programs 1946-1976. In charge of development of Soviet rocketry 1946-1957. Chairman of the VPK 1957-1963. Secretary of Central Committee for Defence and Space 1965-1976.
Ustinov, Nikolai Grigoyevich (1921-) Russian officer. Colonel, worked at NII-4 from 1950 to 1976. After 1976 Senior Scientific Specialist for oceanography at the Academy of Sciences. Managed development of space tracking vessels Komarov, Gagarin, and Korolev.
Utah State U. Space Dynamics Lab, USA
UT.
Universal Time (a.k.a. GMT, or Zulu Time; cf UTC)
UTC.
Coordinated Universal Time (subtly different from UT)
Ute.
The Ute (TU-715) motor was developed from the Genie motor baseline. Later derivatives were combined with booster or upper stages.
Ute.
American sounding rocket. The Ute (TU-715) motor was developed from the Genie motor baseline. Later derivatives were combined with booster or upper stages.
American sounding rocket. Two stage vehicle consisting of 1 x Ute + 1 x Apache
American sounding rocket. The Ute (TU-715) motor was developed from the Genie motor baseline to serve as a first stage booster in the Ute-Tomahawk sounding rocket vehicle. 2 stage vehicle consisting of 1 x Ute + 1 x Tomahawk
Solid rocket stage. 85.00 kN (19,109 lbf) thrust. Mass 200 kg (441 lb).
Utkin, Vladimir Fedorovich (1923-2000) Russian chief designer. Deputy Chief Designer 1961-1971 of Yangel design bureau. Succeeded Yangel as Chief Designer in 1971. After the breakup of the Soviet Union, left the Ukraine in 1990 to become head of TsAGI in Moscow.
Utkin, Ivan Ivanovich (1910-1985) Russian engineer. Chief Designer 1960-1970 of NII IT. Specialised in spacecraft memory data recorders.
Utsch, Albert (1902-1970) German-American design engineer for McDonnell on the Mercury and Gemini spacecraft.
UV.
Ultraviolet
UVS.
UltraViolet Spectrometer
Uzbekistan
Headquarters of an RVSN Division, 1965-present. The division operated 64 heavy ICBM silos (R-36). By the 1990's these were supplemented with 12 RT-23 launchers.
UZKA.
Directorate of the Deputy Commander of Artillery (Russian abbreviation)