HEO倾角长期漂移与控制策略

考虑日月引力对卫星轨道的扰动影响,分析了大椭圆轨道(HEO)倾角漂移规律,推导了小倾角HEO轨道的倾角长期漂移解析公式。结合HEO轨道倾角保持要求,给出了相应倾角控制策略。以STK为比较验证软件平台,经仿真分析与比较可知:文中推导的小倾角HEO轨道的轨道倾角解析公式较STK计算偏差在5%以内,验证了解析公式正确性;基于推导的倾角长期漂移解析公式,进行了倾角控制仿真,仿真结果表明了控制策略的有效性,并同时体现了倾角长期漂移解析计算公式在工程中的作用。

Long-term Evolution and Control of Inclination for High Eccentric Orbit

The inclination will drift because of the inference of solar gravity perturbation and lunar gravity perturbation.The analytic equations for computation of long-term evolution of inclination of HEO with small inclination were deduced.The maintenance strategy of inclination was put forward.The deviation of the inclination,comparing with numeric results calculated by STK,was within 5% which indicate the preciseness of the deduced analytical equations.The simulation of inclination maintenance was also executed.The results show that the maintenance strategy of inclination is effective and the deduced analytical equations have good engineering prospect application.