- 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
"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 上杉 邦憲 川口 淳一郎 横田 博樹 村中 昇 滑 孝和 北出 賢二 小笠原 雅弘 木村 雅文 土橋 雅之 NINOMIYA Keiken UESUGI Kuninori KAWAGUCHI Junichiro YOKOTA Hiroki MURANAKA Noboru NAMERA Takakazu KITADE Kenji OGASAWARA Masahiro KIMURA Masahumi DOBASHI Masayuki
- 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.33, pp.1-45, 1986-03
To support the operation of onboard AOCS (Attitude and Orbit Control System) of "SAKIGAKE" and "SUISEI", ground support software for attitude control and orbit correction was developed. The software, named POPS (PLANET-A AOCS Operation Software), has the function of (1) generating the commands for RCS thruster control and HGA (High Gain Antenna) despin control, (2) simulating spacecraft attitude dynamics to confirm the generated RCS control commands. (3) performing orbit correction analysis to provide the optimum ⊿V-maneuver under various maneuvering constraints, (4) estimating RCS fuel consumption, and (5) conducting the calibration of RCS thrusters. In this paper the functions of POPS are described in detail. The operational results of "SAKIGAKE" and "SUISEI" in orbit are also presented.