摘要
研究航天器的能量/姿控一体化控制系统(IPACS)的设计问题。针对带有4个飞轮(3正交、1斜装)的航天器的IPACS,设计了一个滑动模态姿态控制器。设计了飞轮组的控制律,保证了在储能时,飞轮的转速变化不会对航天器的姿态造成扰动,而且不影响正常的姿态控制,同时实现了姿态控制与能量存储。针对太阳帆板的功率变化特性以及飞轮电机的输入功率限制,提出了一种新的储能功率的规划方案,使飞轮在每个轨道周期内储存和释放的能量达到平衡,同时尽量利用了太阳帆板提供的功率,从而可以有效地减少太阳帆板的面积,减轻太阳帆板的质量。为了验证所设计的IPACS的有效性,给出了一个仿真实例。
This paper presents a design for an integrated power and attitude control system (IPACS) for spacecraft. A sliding mode attitude controller was used for the IPACS of a spacecraft equipped with four (3 orthogonal + 1 skew) wheels. A control law for the wheels guarantees the spacecraft attitude not be perturbed by variation of wheels' rotation during energy storage; thereby realizing simultaneous attitude control and energy storage. A power controller designed for the variable power characteristics of the solar arrays and the input power restrictions of the motors balances the charging and discharging in each orbital cycle. The controller more efficiently uses the power provided by the solar arrays, which reduces the solar array area and mass. Simulations verify the IPACS design.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2005年第2期280-284,共5页
Journal of Tsinghua University(Science and Technology)
基金
中国博士后科学基金项目(中博基2003-03)
国家自然科学基金资助项目(10372011)
关键词
能量/姿控一体化控制系统
滑动模态控制
功率规划
飞轮组的控制律
integrated power and attitude control system (IPACS)
sliding mode control
power programming
control law of wheels
