Internationa1 Organization Document Type: PREPRINT Most documents available from AIAA Technical Library Journal Announcement: IAA8503 The H-I launch vehicle for placing a 550 kg class payload into geosynchronous orbit has been developed by the National Space Development Agency o-f Japan. The second- stage propulsion system of the H-1 consists of a set of tank systems and a liquid hydrogen (LH2)/liquid oxygen (LOX) propellant rocket engine (LE-5) with a 10.5 ton thrust level in vacuum. One of the crucial steps in the development of the second-stage propulsion system involved the conduction of battle ship firing tests (BET). These tests had the objective to verify the functional performance of the integrated propulsion system and to evaluate the design parameters and performance potentials. A description is provided of the test results of the BET. Attention is given to the status of the development schedule, the basic system parameters, and a summary of the BET. (G.R.) Source of Abstract (Subfile): AIAA/TIS Descriptors: *HEAVY LIET LAUNCH VEHICLES; *JAPANESE SPACE PROGRAM; *LIQUID PROPELLANT ROCKET ENGINES; *PRELAUNCH TESTS; *PROF'ULSION SYSTEM PERFORMANCE; HIGH THRUST; LIQUID HYDROGEN; LIQUID OXYGEN; MULTISTAGE ROCKET VEHICLES; ROCKET ENGINE DESIGN; SHIPS Subject Classification: 7520 Spacecraft Propulsion & Power (1975-) Alternative operational modes and cost of removing geostationary satellite debris. THOMAS, U. (Berlin, Technische Universitaet, Berlin, West Germany) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7- 13, 1984. 10 p. 26 Refs. Report No.: IAF PAPER 84-267 Language: Eng1ish. Country of Origin: Germany, Federal Republic of. Country of Publication: International Organization Document Type: PREPRINT Most documents available from AIAA Technical Library Journal Announcement: IAA8503 Possible methods and costs of removing inactive satellites from GEO and preventing further accumulation of useless debris are investigated. The collision hazards arise because of errant, pendulous orbits traveled by satellites depleted of station-keeping propellants. The si mp1est av o i d a n c e method is to fire the last on—board propellants to raise the satellite orbits 500 km, at a cost of 1/2 yr of oper ation. An a11ernat i ve method involves sendinq a spacecraft from LE0 to pickup the inactive satellites and moves them to higher orbits, or return them to a service center in LEO or for a Shuttle return to earth. The development of a heavy lift launch vehicle capable of carrying a large LEO-GEO ferry into LEO is projected to lower GEO satellite retrieval costs to $3 mi 11ion/spacecraft, a negligible figure relative to the costs of industrializing space. (M.S.K.)
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