集群航天器姿-轨耦合动力学与时变控制研究

Fractionated spacecraft rapidly becomes the research emphasis of space agency at domestic and abroad because of on-orbit flexibility, good expansibility and wide application. Firstly, with the deep analysis of motion characteristics on all single function modules of fractionated spacecraft and the system composed by networking, the fractionated spacecraft movement constraints of relative orbit and attitude will be obtained, and the orbit and attitude integrated coupled dynamic model will be established. Secondly, considering the model uncertainty and special requirements of fractionated spacecraft, such as control precision, stability, and control time, the terminal constraint and control time will be introduced to the controller design. Based on the time-varying control theory, the design method of robust time-varying controller with powering performance and high accuracy for fractionated spacecraft will be studied. Finally, combined with the good expansibility and independence of swarm spacecraft,the simulation software of dyanmic and control system will be developed on the HLA structure to verify the correctness and effectiveness of proposed method and also to provide scientific theory foundation of the engineering realization of fractionated spacecraft in the future.

集群航天器具备在轨灵活、可扩展性好和适应面广等特点，迅速成为国内外航天机构研究的重点。本课题首先深入分析集群航天器中单个功能模块和组网后整个系统的运动特点，确定集群航天器相对位置和相对姿态的运动约束，研究建立针对集群航天器的姿态和轨道一体化动力学模型；然后深入研究集群航天器对控制精度、稳定度和控制时间的特殊要求，基于时变控制理论，将终端约束和控制时间纳入控制器设计，并考虑模型不确定性，研究适应于集群航天器快速高精度鲁棒时变控制器的设计和求解方法；最后利用HLA的体系结构优势，结合集群航天器可扩展性、相对独立性好等特点，进行集群航天器动力学与控制系统仿真软件开发，既用来验证课题提出算法的正确性和有效性，又为未来集群航天器的工程应用提供科学理论基础。

集群航天器具有在轨灵活性、可扩展性、可维护性和快速响应能力，研究集群航天器对于加快快速响应空间系统的建设速度，增强空间技术创新能力和提高新型航天器研制水平具有重要意义。首先基于对偶四元数建立了针对集群航天器的姿态和轨道一体化动力学模型，并研究了集群航天器相对姿态与轨道确定方法；然后根据集群航天器对控制精度、稳定度和控制时间的特殊要求，将终端约束、控制时间及模型不确定性纳入控制器设计，基于时变控制理论研究了适应于集群航天器快速高精度鲁棒时变控制器的设计和求解方法；最后利用HLA 的体系结构优势，结合集群航天器可扩展性、相对独立性好等特点，开发了集群航天器动力学与控制系统仿真软件，验证了课题提出算法的正确性和有效性，为未来集群航天器的工程应用提供科学理论基础。