Document Type: JOURNAL ARTICLE Most documents available from AIAA Technical Library Journal Announcement: IAA8503 Three new Soviet launch vehicles are described, including two winged reentry spacecraft. A medium lift launch vehicle, capable of placing more than 15,000 kg in LED, will be used for high launch rates and a man-rated space plane, A heavy-lift launch vehicle configuration in the final development stages is intended'to carry a Shuttle-like craft or 95,000 kg into LEO. An M-4 modified bomber reportedly experienced a runway accident while ferrying the RAM--R orbiter in April 1983. A Saturn-V class heavy lift launch vehicle (HLLV) with a 95 m core stage and six or more liquid fuel strap-on boosters is under launch preparation. The HLLV capacity is projected as 150,000 kg to LEO, or a 100,000 kg space station capable of habitation by 6-12 cosmonauts. The mini-Shuttle will be used to ferry crew and cargo to the space station, and may have an air-breathing propulsion system to extend its range. All launches will be from Tyuratam. (M.S.K.) Source of Abstract (Subfile): AIAA/TIS Descriptors: *HEAVY LIFT LAUNCH VEHICLES; *LAUNCH VEHICLE CONFIGURATIONS; *S0VIET SPACECRAFT; *SPACE SHUTTLES; MANNED SPACE FLIGHT; REENTRY VEHICLES Subject Classification: 7516 Space Transportation (1975--) The HM60 project. POULIQUEN, M. F. (Societe Europeenne de Propulsion, Vernon, Eure, France) ; BORROMEE, J. (Centre National d'Etudes Spatiales, Evry, Essonne, France) International Astronaut!cal Federation, International Astronaut!cal Congress, 35th, Lausanne, Switzerland, Oct. 7-13, 1984. 7 p. Research supported by the Centre National d'Etudes Spat i ales. Report No.: IAF PAPER 84-308 Language: Eng11sh. Country of Origin: France. Country of Publication: International Organi zati on Document Type: PREPRINT Most documents available from AIAA Technical Library Journal Announcement: IAA8503 The Ariane V configuration consists of two solid propellant boosters and a large cryogenic core powered by one HM60 engine. The engine is ignited prior to liftoff. During the initial ascent phase, it operates in parallel with the two solid boosters. The HM60 operational requirements have to be compatible with overall Ariane V objectives. These objectives are related to low-cost hardware and operation, an achievement of operational capability in 1995, high reliability, man-rating capability, and low-cost development. Attention is given to the basic requirements regarding the HM60 engine, criteria used for the selection of the engine design, the development and testing principles, the thrust chamber, the injector model test program, and the turbopumps. (G.R.) Source of Abstract (Subfile): AIAA/TIS Descriptors: *ARIANE LAUNCH VEHICLE; *CRYOGENIC ROCKET PROPELLANTS; *DESIGN TO COST; *HEAVY LIFT LAUNCH
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