CAJ | 학술논문

应用螺旋理论对航天器相对轨道与姿态运动进行了研究。针对航天器相对运动过程中存在的姿态轨道耦合问题：基于刚体假设，推导建立了基于螺旋对偶式的航天器姿轨耦合相对运动模型；分析给出了航天器相对运动过程中姿态轨道的耦合效应；针对所建模型的强耦合、非线性特性，在控制律设计时采用了非线性前馈控制，最后进行了数值仿真，结果表明了该模型和控制律的有效性，可为工程应用提供参考。
응용라선이론대항천기상대궤도여자태운동진행료연구。침대항천기상대운동과정중존재적자태궤도우합문제：기우강체가설，추도건립료기우라선대우식적항천기자궤우합상대운동모형；분석급출료항천기상대운동과정중자태궤도적우합효응；침대소건모형적강우합、비선성특성，재공제률설계시채용료비선성전궤공제，최후진행료수치방진，결과표명료해모형화공제률적유효성，가위공정응용제공삼고。
Considering the strong coupling between the orbit and attitude of two spacecraft in relative motion , based on the assumption of rigid body dynamics and the screw theory , we deduce and establish their orbit and attitude coupling dynamics model and analyze the orbit and attitude coupling effect .Considering that the dynamics model is strongly coupled and nonlinear , we design its nonlinear feedforward control law , which has a good control precision and stability and is suitable for the short-distance and in-orbit operations that have time constrains .We simulate the effectiveness of the orbit and attitude coupling dynamics model and the nonlinear feedforward control law ;the simu-lation results, given in Fig.1 through 6, and their analysis show preliminarily that:(1) both the relative speed and angular speed of the two spacecraft converge to zero , there being no change in their relative position and attitude and the whole control process reaching the desired value within 200 seconds; ( 2 ) the orbit and attitude coupling model we thus designed can be used for spacecraft′s short-range randezvous and the nonlinear feedforward control law can satisfy the precision requirements for in-orbit operations .