多模式混合推进悬停控制与半物理仿真系统

Semi-physical simulation system for hovering control with multi-mode hybrid propulsion

随着空间任务复杂度的提高,相对运动控制地面验证系统的设计难度日益增加,尤其对于地球静止轨道卫星,相对运动构型涉及伴飞、绕飞、悬停等各种形式。针对静止轨道卫星悬停控制的新需求,基于相对轨道参数描述方法,采用半长轴差和偏心率差两个参数对面内“水滴”悬停构型的形成进行了深入研究,提出了一种多模式混合推进模式下的面内悬停两参数设计方法,并设计了一套通用的空间运动仿真验证系统,位置精度达毫米量级。对该构型的制导控制律进行了半物理验证,半实物仿真位置估计误差约为20 m(3σ),结果表明制导控制律正确,所提出的验证方法可推广应用于其它相对运动控制技术的地面验证。

As the complexity of space missions increases,the design of the ground verification system of relative motion control becomes increasingly difficult,especially for geostationary satellites,whose relative motion configuration involves various flight forms such as accompanying flight,circling flight,and hovering,etc.Aiming at the new requirement of hovering control of geostationary orbit satellites,the formation of the“drip”hovering configuration in the plane is studied by using the parameters of semi-long axis difference and eccentricity difference based on relative orbital parameters description method.A two-parameter design method of in-plane hovering in multi-mode hybrid propulsion mode is proposed,and a general space motion simulation verification system is designed with the positional accuracy being in the order of millimeter.Semi-physical tests for the configuration guidance control law are carried out,which show that the semi-physical simulation position estimation error is about 20 m(3σ),the guidance control law is correct,and the proposed verification method can also be applied to the ground of other relative motion control techniques.