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针对太阳帆、太阳电混合推进航天器日心悬浮轨道保持控制问题进行了研究。为解决基于局部线性化模型设计轨道保持控制器时存在的控制精度不高、模型精确性过度依赖等问题,应用自抗扰控制(ADRC)技术设计了轨道保持控制器。首先,采用圆形限制性三体问题(CRTBP)模型推导了混合小推力航天器日心悬浮轨道动力学方程;然后,考虑系统模型不确定性和外部扰动,提出了一种基于扰动估计和补偿的轨道保持控制方法;最后,数值仿真表明存在系统模型不确定性、初始入轨误差及地球轨道偏心率扰动等因素的情况下,所设计的控制器仅需很小的速度增量即可实现高精度的日心悬浮轨道保持控制。
Aiming at the solar sail and solar hybrid propulsion spacecraft heliostat suspended orbit keeping control problems were studied. In order to solve the problems of low control accuracy and over-reliance on model accuracy when designing a track-keeping controller based on a local linearized model, an orbit-keeping controller is designed by using ADRC technology. First of all, based on the CRTBP model, the kinetic equation of the hovering orbit of hybrid small-thrust spacecraft is derived. Then, considering the uncertainties of the system model and external disturbances, a new method based on disturbance estimation and compensation Finally, numerical simulations show that the proposed controller can be realized with only a small incremental speed in the presence of uncertainties of the system model, initial orbital errors, and orbital eccentricity disturbances. High-precision heliocentric suspension orbit control.