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H-1

The first stage of the H-I was essentially the same as that of the N-II with a liquid oxygen/kerosene main engine and 6-9 small solid-propellant strap-on boosters. The second stage was of Japanese origin, built by Mitsubishi Heavy Industries, and burned liquid oxygen and liquid hydrogen. A small solid-propellant third stage designed by Nissan was employed on GEO missions to place the payload (up to 1,100 kg) into GTO (References 116 and 125). The H-I program concluded in 1992 with nine successes and no failures.

To provide greater payload capacity and to permit unencumbered commercial space transportation offerings (the Delta licensing agreement restricted the use of the H-I for commercial flights), Japan developed the H-II launch vehicle based on all-Japanese propulsion systems. The H-II can lift payloads four times heavier than the H-I into LEO (up to 10 metric tons) and GTO (up to 4 metric tons) and will open the door to NASDA spacecraft designed to explore the Moon and planets. The first mission on 3 February 1994 deployed one payload into LEO and then carried an experimental package VEP (Vehicle Evaluation Payload) to GTO. The next H-II mission on 28 August deployed the 3.8 metric ton ETS-VI spacecraft.

H-1 (Japan)

Background Information First Launch: August 1986 Flight Rate: 2 per year Launch Site: Tanegashima Capability: 1,210 lb to GEO 4,840 lb to LEO History Japanese rocket program began in late 1950's Developed and launched by the National Space Development Agency of Japan (NASDA) H-I is a derivative of the earlier N-I and N-2 vehicles Description Three-stage vehicle with solid strap-on boosters Stage 1 burns RJ-1 (kerosene) in a MHI Rocketdyne MB-3 engine providing a thrust of 169,900 lb Stage 2 burns LOX/H2 in a MHI LE-5 engne providing a thrust of 23,100 lb Stage 3 burns HTPB composite grain fuel providing a thrust of 17,400 lb Maximum of nine strap-on boosters (normally six) Thiokol TX-354-S Castor 2s providing a thrust of 49,600 lb each Profile Length: 132 ft Launch Weight: 306,500 lb Diameter: 8 ft Liftoff Thrust: 467,500 lb Payload Fairing: 26 ft x 8 ft

References

• 116. Space In Japan 1988-89, Research and Development Bureau, Science and Technology Agency, Tokyo, 1988.
• 117. M. Oda and Y. Tanaka, "Japan's Blossoming Space Science", Sky and Telescope, January 1987, pp. 7-11.
• 118. C. Covault, "Japan Designing Atlas-Class Rocket To Launch Lunar, Planetary Missions", Aviation Week and Space Technology , 20 August 1990, pp. 63-68.
• 119. K. P. Dawson, "Japanese M-5 Faces Delay to '95 Start", Space News, 15-21 June 1992, p. 4.
• 120. "Japan Presses on With M-5 Project Despite Motor Casing Problems., Aviation Week and Space Technology, 10 August 1992, pp. 48-49.
• 121. J. Onoda et al, "Structural Development Status of Japanese Next Generation Launcher for Scientific Satellites", Paper IAF-93-1.2.208, 44th Congress of the International Astronautical Federation, 16-22 October 1993.
• 122. Kvodo News Service, Tokyo, 21 June 1994.
• 123. E. Sekigawa, "Japan Confirms Delays in M-5 Booster Launch", Aviation Week and Space Technology, 27 June 1994, p. 82.
• 124. M. Mecham, "Japan's Launch Capacity to Grow with J-1, M-5", Aviation Week and Space Technology, 20 March 1995, pp. 57-58.
• 125. NASDA. National Space Agency of Japan, NASDA, 1994.
• Adapted from: Europe and Asia in Space 1993-1994, Nicholas Johnson and David Rodvold [Kaman Sciences / Air Force Phillips Laboratory]