1992•Unpublished venueRequires access
Development of electrical power subsystem for SOLAR-A and ASTRO-D
Masaaki Igarashi, Masaji Honma, Eisaku Hayashi, Yoichi Takizawa, Yukishige Nozaki, Yo Tanaka, Y. Ogawara, Tadashi Takano, Hirobumi INOUE, Michio Tajima, K Takahashi
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Abstract
The scientific satellite SOLAR-A to mainly observe solar flare phenomena with x-ray was launched by M-3SII-6 rocket in August 1991 and has been operated successfully for over seven months. This is the first regulate power bus satellite in Japan's scientific satellites. This electrical power subsystem equipped with solar arrays and batteries has supported the successful mission operation as expected. In addition, the next scientific satellite ASTRO-D employs the same electrical power subsystem as SOLAR-A does. This paper describes the design of electrical power subsystem for these satellites and the flight performance of the electrical power subsystem for SOLAR-A. The electrical power subsystem for SOLAR-A has 250W class output capability in the eclipse period. On the other hand, the electrical power subsystem for ASTRO-D is more lightweight and consists of the regulated and unregulated bus lines. From the flight data of SOLAR-A, adequacy of standard design of electrical power subsystems for small size satellites with 300W class power capability was able to be verified. 1 ref., 5 figs., 3 tabs.