Abstract With a focus on a number of state-of-the-art techniques in the area of autonomous non-rigid space systems control, realization of a comprehensive strategy is worthy of investigation to handle a set of parameters of the present overactuated processes with model uncertainties. In a word, the subject behind the research is to guarantee the desirable performance of a class of the autonomous space systems, which can be considered through the moments of inertia, the central of mass, the profile of the thrust vector and the misalignments of the propellant engine to deal with mission operation plans. There is the attitude cascade strategy including the low thrust three-axis engine off mode control, the low thrust x -axis engine on mode control and finally the high thrust y , z -axis engine on mode control, respectively. The control strategy is realized in a number of loops, as long as the on and off modes of the propellant engine are focused on the Euler angles control, in finite burn time, and quaternion vector control, in non-burn time, respectively, in line with parameters variations. It is to note that the parameters variations are coherently different in each one of the engine modes. The dynamics of high-low thrusters are taken into real consideration, where the control allocations in association with the pulse-width pulse-frequency modulators are employed to cope with a set of on–off reaction thrusters. The investigated results are finally analyzed in line with some related well-known benchmarks to verify the approach performance. The main contribution and motivation of the strategy investigated here is to propose a novel three-axis comprehensive cascade robust control solution to be able to deal with the parameters of autonomous non-rigid space systems under control with model uncertainties, in a synchronous manner, once the results regarding the tracking of the three-axis referenced commands are efficient with high accuracy along with the recent potential outcomes, researched in this area.

中文翻译：

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考虑一类具有模型不确定性的过驱动自主非刚性空间系统的综合串级控制策略

摘要 关注自主非刚性空间系统控制领域的一些最先进技术，实现一个综合策略是值得研究的，以使用模型处理当前过驱动过程的一组参数。不确定性。总之，研究背后的主题是保证一类自主空间系统的理想性能，这可以通过惯性矩、质心、推力矢量的轮廓和不对齐来考虑。推进剂发动机处理任务运行计划。姿态级联策略包括低推力三轴发动机关闭模式控制、低推力 x 轴发动机开启模式控制以及最后的高推力 y、z 轴发动机开启模式控制。控制策略是在多个循环中实现的，只要推进剂发动机的开和关模式分别专注于有限燃烧时间的欧拉角控制和非燃烧时间的四元数矢量控制，在符合参数变化。需要注意的是，在每种发动机模式中，参数变化是一致不同的。实际考虑了高低推进器的动力学，其中使用与脉宽脉冲频率调制器相关的控制分配来应对一组开关反应推进器。最后根据一些相关的知名基准对调查结果进行分析，以验证方法性能。