基于螺旋理论的航天器姿轨耦合分析

针对航天器运动姿轨耦合性问题,对基于螺旋理论得到的航天器运动模型,定性地分析了姿轨耦合特性。采用参数分析法,从模型所包含的耦合项出发,逐次改变各个参数,进而推导出对应的耦合表达式。为了检验耦合性对控制效果的影响,设计了PD 控制律并进行数值仿真。理论分析和仿真结果进一步证明,基于螺旋理论的航天器姿轨模型,其姿态和轨道运动之间是相互影响的,从控制角度而言,姿态运动对轨道运动影响相对更为严重,容易出现了大的振荡,而轨道运动对姿态运动的影响基本可以忽略,为工程实践提供参考。

Coupling Analysis of the Spacecraft Attitude and Orbit Model Based on the Spiral Theory

The coupling between spacecraft attitude and orbit movement in an integrated model based on the spiral theory was analyzed.The method parameters analysis method was used,which changed the coupling parameters successively,to get the curves and the laws of coupling terms.The validity of theoretical analysis was proved.To verify the coupling impact on the control effect,the control law was designed.The result shows that the coupling seriously affects the attitude and the orbit of relative motion,and the attitude influences the orbit motion a lot,and can converge easily,while the orbit has little effect on the attitude.