CAJ | 학술논문

针对具有自主接近能力的航天器开展了反交会规避机动方法研究。建立了仅测角相对导航模型，随后利用状态估计误差给出了可观测度的定义，量化了可观测性指标。以可观测度为评价指标，提出基于虚拟轨道的可观测度计算方法，以可观测度梯度对规避机动方向进行优化，保证了规避机动使目标航天器的可观测性达到最大弱化，并给出了规避机动大小计算方法。给出了仿真算例，结果表明提出的方法能够使系统的可观测性明显减弱，达到了设计要求，为规避机动研究提供了一种新视角。
침대구유자주접근능력적항천기개전료반교회규피궤동방법연구。건립료부측각상대도항모형，수후이용상태고계오차급출료가관측도적정의，양화료가관측성지표。이가관측도위평개지표，제출기우허의궤도적가관측도계산방법，이가관측도제도대규피궤동방향진행우화，보증료규피궤동사목표항천기적가관측성체도최대약화，병급출료규피궤동대소계산방법。급출료방진산례，결과표명제출적방법능구사계통적가관측성명현감약，체도료설계요구，위규피궤동연구제공료일충신시각。
An anti-rendezvous evasion maneuver method is proposed in order to escape from the spacecraft that has autonomous approaching ability.Supposing that a two impulse C-W navigation strategy is used by the approaching spacecraft,first a bearing-only relative navigation model is built.Then,a definition of degree of observability based on state estimation error is proposed so as to quantify observability.By using the degree of observability conception,the evasion maneuver direction is chosen as its gradient,which guarantees that every unit impulse can reduce the system observability mostly.Finally,the numerical simulation is conducted with different maneuver impulse,and the result shows that the method proposed can attenuate the system observability obviously.The method offers a new viewpoint for evasion maneuver research.