基于优化的羽流撞击消旋技术瞄准策略设计

针对自由翻滚目标卫星的消旋问题，使用化学推力器羽流撞击的方式进行消旋具有较高的可行性和安全性。当目标太阳翼法线与星本体自旋轴存在一定夹角时，需要对消旋推力器的瞄准策略进行设计，以提高控制精度和系统效率。目前国内外对于一般情况下瞄准策略的设计仍存在空白。基于参数化羽流撞击模型，对空间目标的动力学特性进行分析并给出典型工况，分析了羽流撞击力对相对位置姿态的敏感性，得到了瞄准策略设计的一般性准则，在此基础上设计了瞄准策略优化模型的完整表达。仿真计算表明，该瞄准策略适用于太阳翼法向相对期望消旋力矩方向存在一定夹角的情况，并且在保证力矩幅值较大的条件下令精度达到10°以内。该方法适用于太阳翼相对自旋轴倾斜和存在章动运动的目标卫星，从而为服务平台控制系统设计提供支持。

An optimization-based pointing strategy design of plume impingement detumbling technology#br#

In view of on-orbit capturing for free-tumbling uncooperative targets, to de-tumble the target using plume impingement force will improve the safety and feasibility of capture mission. The pointing strategy is required under the circumstance that the solar array norm is inclined from spin axis. Pointing strategy design is blank still. The optimization of pointing strategy will benefit the accuracy and efficiency of the system. A parametric plume impingement model was built, then a working condition was proposed based on typical targets, and the sensitivity of de-tumbling torque to relative position and attitude was given. Finally, by designing the target function, the model of pointing strategy was built. Simulations show that the pointing strategy is suitable for situations that solar array slopes at an angle with desired torque, and the accuracy is improved to 10 degrees with a relatively large torque. The method is feasible for spin target with a rotation of solar panel relates to spin axis and the target with nutation motion, and the research will support service vehicle’s control system design.