著者

二宮 敬虔 上杉 邦憲 村中 昇 加藤 昭夫 北出 賢二 滑 孝和 卯尾 匡史 NINOMIYA Keiken UESUGI Kuninori MURANAKA Noboru KATOH Akio KITADE Kenji NAMERA Takakazu UO Masashi

出版者

宇宙科学研究所

雑誌

宇宙科学研究所報告 (ISSN:02852853)

巻号頁・発行日

vol.37, pp.1-62, 1986-06

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"SAKIGAKE", Japan's first interplanetary spacecraft was successfully launched on January 8,1985.Its mission was to verify the launch capability of the then newly developed Mu-3SIIvehicle and the technology applied to "SUISEI", Japan's Halley's comet explorer launched later the same year on August 19. These spacecraft are spin-stabilized at about 6rpm spin rate, and have same configuration except, of course, for the differing scientific payloads. To assure the communication link between the spacecraft and the ground station, a high-gain parabolic antenna mechanically despun with respect to the spinning spacecraft, is used. In order to provide SUISEI with the ability for ultraviolet imagery of the comet, while satisfying, thermal constraints of the onboard instruments, the spacecraft were also designed so that their spin-rate could be reduced to a low and stable value of around 0.2rpm by spinning up a momentum wheel. The imagery instrument uses the time-delay-and-integration scheme of a 2-dimensional charge coupled device sensor to obtain unblurred pictures of the comet at this spacecraft spin rate. For attitude and orbit control actuator, a hydrazine (N_2H_4) monopropellant propulsion system was developed. Attitude sensors consist of a spin-type sun sensor and a star scanner. Thus far, the attitude and orbit cotrol systems have functioned properly so these spacecraft should be able to fully complete their mission goals. In this report, the function and the detailed design of the attitude and orbit control system of SAKIGAKE and SUISEI are described, together with the analyses pertinent to the design and the operation. The flight results to verify the design are also presented.

著者

二宮 敬虔 広川 英治 周東 晃四郎 村中 昇 卯尾 匡史 小笠原 雅弘 青木 星子 NINOMIYA Keiken HIROKAWA Eiji SHUTO Koshiro MURANAKA Noboru Uo Masashi OGASAWARA Masashi AOKI Hoshiko

出版者

宇宙科学研究所

雑誌

宇宙科学研究所報告 (ISSN:02852853)

巻号頁・発行日

vol.32, pp.1-37, 1986-03

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An Attitude Determination Software (ADS) system was developed for Japan's first interplanetary spacecraft, "SAKIGAKE (1985-001-A)" and "SUISEI (1985-073-A)". The ADS determines the direction of the spaceraft's spin-axis in and inertial reference frame based on telemetry data received from the onboard sun sensor and star scanner. The software system sonsists of three functional subsystems : ADS-RT, ADS-DT, and ADS-BIAS. These are used respectively for near real-time attitude determination, off-line attitude determination, and bias estimation of onboard attitude sensors. In this paper the authors describe the ADS system configuration, its functions, adopted principles of attitude and bias estimation, and the operational results obtained through the in-orbit operations of "SAKIGAKE" and "SUISEI".