Guidance method and guidance system applied to laser/satellite composite aircraft

The invention discloses a guidance method and guidance system applied to a laser/satellite composite aircraft, and the method comprises the steps: employing a proportional guidance law for a middle guidance section of the aircraft, employing a re-compensation proportional guidance law for a terminal guidance section of the aircraft, and achieving the falling angle constraint through setting a reasonable gravity compensation coefficient for the terminal guidance section, and adopting a handover guidance law resolving method in a handover section of the middle guidance section and the terminal guidance section, so that sudden change of guidance instructions and flight paths is avoided, and the whole flight process of the aircraft is stable. 本发明公开了一种应用于激光/卫星复合飞行器的制导方法及制导系统，该方法中，飞行器中制导段采用比例导引制导律，飞行器末制导段采用重补比例导引制导律，末制导段通过设置合理的重力补偿系数来实现落角约束，在中制导段和末制导段交接的交接段内采用交接的制导律解算方法，从而避免制导指令及飞行轨迹突变，使得飞行器整体飞行过程平稳。