航天器抗攻击规避方法研究

Research on Attack Avoidance for Spacecraft

首先基于相对轨道要素建立了满足一定精度要求的两飞行器相对运动动力学模型。考虑主要摄动因素以及航天器、未知目标的运动关系。利用航天器上微波雷达等设备测量航天器与未知目标之间的相对距离、高低角和方位角,以及相应的变化率,据此可以计算出被测量目标的相对位置和相对速度,进而计算航天器与未知目标之间的相对轨道要素,实现相对导航。当未知目标轨迹被识别后,根据预警策略判断未知目标是敌意的、非敌意的,并且判定航天器需要规避或暂时不需要规避。并且本文基于相对轨道要素提出了规避轨道机动策略,航天器可以远离未知目标,伴随未知目标飞行,跟随未知目标飞行,机动回到初始飞行轨道,等等。最后,利用Simulink对航天器相对轨道运动、轨道规避预警方案、自主相对导航方案、轨道规避控制策略进行了建模。选取了典型的未知目标攻击和航天器规避算例,从仿真结果可以看出,本文所述规避方法是可行性的。

This paper first presents a relative motion dynamics model for two spacecraft based on relative orbit elements, with a certain precision requirement, as a starting point for further related computation and research. The main perturbation factors .and the relationship between the spacecraft and the unidentified object are taken into account. The range, elevation angle, azimuth angle and their rates are to be measured by microwave radars or other instruments fixed on the spacecraft to obtain the relative position, relative velocity and relative orbit elements, and to realize relative navigation. After the determination of an unknown object＇s trajectory, a judgment is made by alert strategy to decide whether it is hostile or not and whether one has to avoid it or not. The avoidance orbit maneuver strategy is discussed based on relative orbit elements, with respect to the realization of keeping away from object, going with object, following object, transferring to initial orbit, etc. The relative motion, avoidance alert strategy, autonomous relative navigation and avoidance control strategy are implemented by Simulink for typical cases to show the avoidance method＇s feasibility