STUDY ON THE SUBATMOSPHERIC BURNING RATE CHARACTERISTICS OF COMPOSITE PROPELLANTS

Kazushige Kato; Motoyasu Kimura; Masahiro Kohno; Kiyokazu Kobayashi

doi:10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.600

International Journal of Energetic Materials and Chemical Propulsion

Editor en Jefes: Keiichi Hori (open in a new tab) John Zevenbergen (open in a new tab)

Redactor Fundador: Kenneth K. Kuo (open in a new tab)

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 2150-7678

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STUDY ON THE SUBATMOSPHERIC BURNING RATE CHARACTERISTICS OF COMPOSITE PROPELLANTS

Volumen 3, Edición 1-6, 1994, pp. 624-633

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.600

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Kazushige Kato
Research & Development Department, Taketoyo-Plant, NOF Corporation, 61-1 Kitakomatsudani Taketoyo-cho, Chita-gun, Aichi-ken 470-2398 Japan

Motoyasu Kimura
NOF Corporation, Yebisu Garden Place Tower, 20-3, Ebisu 4-chome, Shibuya-ku, Tokyo, 150-6019, Japan

Masahiro Kohno
Institute of Space and Astronautical Science, 3-1-1 Yoshinodai Sagamihara, Kanagawa 229, Japan

Kiyokazu Kobayashi
Institute of Space & Astronautical Science/Japan Aeropace Exploration Agency (JAXA), Japan

SINOPSIS

The Institute of Space and Astronautical Science (ISAS) is undertaking development of its newest satellite launcher, M-V. HTPB-based highly aluminized composite propellents have been developed, and the subatmospheric burning rate characteristics of these propellents were investigated to properly anticipate the thrust decay behavior into the residual thrust region of each stage motor. A simple but unique method was employed in the measurements. The size of the propellent specimen was quite small; 8 mm long and 8 mm in diameter. Ignition was detected by a photo-transistor, and burnout by an ion probe or a fine thermocoupie.

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