VEHICLES; *ROCK.ET ENGINE DESIGN; BOOSTER ROCKET ENGINES; COST REDUCTION; HIGH THRUST; LOW COST; SOLID PROPELLANT ROCKET ENGINES Subject Classification: 7520 Spacecraft Propulsion & Power (1975-) Hydrazine reaction control subsystem for second stage of H-I launch vehicle. KON-NO, A.; IIDA, C. ; NAGASHIMA, R. (National Space Development Agency of Japan, Tokyo, Japan); SHIMIZU, S. (Ishikawajima—Harima Heavy Industries Co., Ltd., Tokyo, Japan) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7— 13, 1984. 8 p. Report No.: IAF PAPER 84-306 Language: Eng1ish. Country of 0rigin: Japan. Country of Pub1ication: Internationa1 0rganization Document Type: PREPRINT Most documents availsb1e from AIAA Technica1 Library Journa1 Announeement: IAA8503 A mon opr ope11 ant hydrazine propu1s i on s ystem h as been developed as the Reaction Control Subsystem (RCS) of the H-I second stage. This subsystem provides the second- stage attitude contro1 and prope11ant sett1ement/retention. It comprises two modules, each of which has one or two propellant tanks and six thrusters. The different RCS feed systems are designed respectively to provide functions in the geostationary- transfer-orbit (GTO) mission and in the low-earth-orbit (LEO) mission. The RCS is of regulated pressure feed in the LEO mission, while a blow-down feed system is selected for the GTO mission on account of the different total-impulse requirement. The modu1e has been tested and qua1ified to the H-I requirement. This paper describes the design, the performance and the state of development of the RCS and its components. (Author) Source of Abstract (Subfi1e): AIAA/TIS Descriptors: *C0NTR0LLED SYSTEMS DESIGN; *HEAVY LIFT LAUNCH VEHICLES; *HYDRAZINE ENGINES; *PR0PULSI0N SYSTEM PERFORMANCE; *REACTI0N CONTROL; BROCKET ENGINE CONTROL; MONOPROPELLANTS; MULTI STAGE ROCKET VEHICLES; PROPELLANT TANKS; ROCKET ENGINE DESIGN Subject Classification: 7520 Spacecraft Propulsion Power (1975-) Battle ship firing test for second stage propulsion system of H-I launch vehicle. KOYARI, Y.; SHIBUKAWA, K.; DENDA, Y.; KATAGI, T. (National Space Development Agency of Japan, Tokyo, Japan) International Astronautical Federation, International Astronautical Congress, 35th, Lausanne, Switzerland, Oct. 7— 13, 1984. 7 p. Report No.: IAF PAPER 84-305 Language: Eng1ish. Country of Origin: Japan. Country of Publication:
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