Attitude Determination and Control System for the PROCYON Micro-Spacecraft
Attitude Determination and Control System for the PROCYON Micro-Spacecraft
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DOI：
10.2322/tjsass.60.181
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发表时间：
2017
影响因子：
1.1
通讯作者：
S. Ikari;T. Inamori;Takahiro Ito;Kaito Ariu;K. Oguri;Masataka Fujimoto;S. Sakai;Y. Kawakatsu;R. Funase
中科院分区：
文献类型：
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作者：
S. Ikari;T. Inamori;Takahiro Ito;Kaito Ariu;K. Oguri;Masataka Fujimoto;S. Sakai;Y. Kawakatsu;R. Funase
本文介绍了世界上第一个行星际微型航天器PROCYON的姿态确定和控制系统（ADCS）的研制策略和在轨结果。PROCYON的高级使命目标是光学导航或小行星近距离飞越。虽然地球轨道的微小卫星已经有了用于实际任务的ADCS，但由于其轨道空间环境的差异，这些ADCS不能用于行星际微小航天器。为了发展一种新的实用的ADCS，四个问题的实用行星际微型航天器进行了讨论：初始太阳捕获没有磁性组件，角动量管理使用一种新的推进系统，鲁棒性实现使用故障检测，隔离，和恢复（FRESH）系统，和精确的姿态控制。这些问题尚未在行星际微型航天器的轨道上得到证明。为了克服这些问题，作者开发了一种可靠而精确的ADCS，一种没有磁性组件的FADCS系统和地基评估系统。在发射前，利用开发的地面评价系统对这四个问题进行了评价。此外，还成功地在轨道上进行了演示。文中给出了所研制的姿态控制系统的结构、仿真和在轨结果。
This paper describes development strategies and on-orbit results of the attitude determination and control system (ADCS) for the world’s first interplanetary micro-spacecraft, PROCYON, whose advanced mission objectives are optical navigation or an asteroid close flyby. Although earth-orbiting micro-satellites already have ADCSs for practical missions, these ADCSs cannot be used for interplanetary micro-spacecraft due to differences in the space environments of their orbits. To develop a new practical ADCS, four issues for practical interplanetary micro-spacecraft are discussed: initial Sun acquisition without magnetic components, angular momentum management using a new propulsion system, the robustness realized using a fault detection, isolation, and recovery (FDIR) system, and precise attitude control. These issues have not been demonstrated on orbit by interplanetary micro-spacecraft. In order to overcome these issues, the authors developed a reliable and precise ADCS, a FDIR system without magnetic components, and ground-based evaluation systems. The four issues were evaluated before launch using the developed ground-based evaluation systems. Furthermore, they were successfully demonstrated on orbit. The architectures and simulation and on-orbit results for the developed attitude control system are proposed in this paper.