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针对使用固体火箭发动机进行卫星快速变轨机动时的姿态翻转问题,提出使用二维质量矩控制技术予以解决。首先分析了喷气阻尼力矩对三轴稳定卫星姿态的影响,随后建立了考虑推进剂燃烧过程的完整动力学模型,并从通道耦合以及扰动力矩角度对模型特性进行了分析;最后利用仿真手段对质量矩控制卫星姿态的可行性进行了仿真分析,同时考察了发动机不同装药形式以及外形尺寸对控制系统操纵性能的影响。结果表明:二维质量矩控制卫星姿态是切实可行的,且短粗型的发动机结构对控制系统设计更加有利。
In order to solve the problem of attitude inversion when using a solid rocket motor to conduct rapid orbit maneuvering of satellites, a two-dimensional mass moment control technique is proposed to solve the problem. Firstly, the influence of jet damping torque on the attitude of the three-axis stabilized satellite was analyzed. Then a complete dynamic model considering the combustion process of propellant was established, and the characteristics of the model were analyzed from the perspective of channel coupling and disturbance torque. Finally, Moment control satellite attitude is simulated and analyzed. At the same time, the effect of different charge forms and dimensions of the engine on the controllability of the control system is investigated. The results show that the two-dimensional mass moment control satellite attitude is feasible, and the stubby engine structure is more beneficial to the control system design.