Fan Ruichao, Chen Xueqin, Liu Ming, Cao Xibin
School of Astronautics, Harbin Institute of Technology, Harbin, 150001, China.
ISA Trans. 2022 May;124:338-348. doi: 10.1016/j.isatra.2020.10.062. Epub 2020 Nov 9.
In this paper, the event-triggered integrated attitude and orbit control problem is studied for the distributed spacecraft formation system. First, the operation rules of dual numbers and dual quaternion are presented, and the attitude-orbit coupling error dynamics models for single spacecraft and spacecraft formation are established based on the dual quaternion. An event-triggered attitude-orbit coupled sliding mode tracking control law is proposed to stabilize the attitude-orbit control system, which can reduce the communication burden among spacecraft at the same time. Under the developed control scheme, the state trajectory of attitude-orbit control systems can arrive on the designed sliding surface in finite time, and the asymptotic stability of the overall formation control system can be ensured. Considering the fact that the inertia and mass parameters in practice may not be measured exactly, an adaptive sliding mode control law is further proposed. Finally, a simulation example is given to verify the validity and feasibility of the proposed spacecraft event-triggered control method.
本文研究了分布式航天器编队系统的事件触发集成姿态与轨道控制问题。首先，给出了对偶四元数的运算规则，并基于对偶四元数建立了单航天器和航天器编队的姿态-轨道耦合误差动力学模型。提出了一种事件触发的姿态-轨道耦合滑模跟踪控制律来稳定姿态-轨道控制系统，同时可以减轻航天器之间的通信负担。在所提出的控制方案下，姿态-轨道控制系统的状态轨迹能够在有限时间内到达设计的滑模面，并确保整个编队控制系统的渐近稳定性。考虑到实际中惯性和质量参数可能无法精确测量，进一步提出了一种自适应滑模控制律。最后，给出了一个仿真算例，验证了所提出的航天器事件触发控制方法的有效性和可行性。
