轨道根数偏差修正的脉冲控制比较研究

Comparisons of Pulse Controls for Orbit Element Error Modification

针对研究卫星轨道根数偏差修正的控制问题。以高斯摄动方程和J2摄动下平均轨道偏差与密切轨道偏差的转换关系为理论基础,采用合适的控制策略,通过对密切轨道根数偏差的控制,实现了对平均轨道根数偏差的修正,数值仿真验证了方法的有效性和正确性。结果表明,控制耦合以及轨道根数偏差之间的相互作用等情况会延长轨道偏差修正所需时间,与将平均轨道根数偏差近似成密切轨道根数偏差的方法相比,基于平均轨道根数偏差的修正方法不但具有工程实现方面的简易性,而且具有更高的控制精度和更少的控制燃料消耗。

The problem of orbit element error modification was researched. Based on Gauss＇ s perturbation equations and the transformation relations under J2 perturbation for osculating and mean orbit element errors, the mean orbit element errors were modified by controlling osculating orbit element errors with appropriate method. Mathematical simulation proved the validity of the given method. The results showed that the control coupling and the interactions among orbit element errors may elongate the error modifications. And compared with the method of regarding mean orbit element errors as osculating orbit element errors, the given method is simple in engineering and better in accuracy with less fuel consumption for eliminating mean orbit element errors.