满足多约束的主动段能量管理制导方法

高超音速飞行器运载任务需要满足多项约束条件,针对耗尽关机型固体运载火箭需要在主动段进行能量管理.基于控制推力和速度之间夹角来实现主动段能量管理的思路,综合交变姿态控制能量管理(AEM,Alternate Attitude Control Energy Management)和一般能量管理(GEM,General Energy Management),提出了样条能量管理(SEM,Spline Energy Management)制导方法,并针对分离前定轴飞行约束条件进行了修正.以三级运载火箭为例,通过AEM,GEM和SEM对比,验证了样条能量管理制导方法的可行性.

Energy management ascent guidance algorithm with multiple constraints

The ascent guidance for hypersonic vehicle launch mission needs to satisfy multiple constraints.For the solid-powered launch vehicle without burn control,energy management was applied to satisfy the constraints.To achieve the energy management,the basic idea is to control the angle between the thrust and the velocity.Based on the alternate attitude control energy management(AEM) and the general energy management(GEM),the spline energy management(SEM) guidance was proposed,and modified for the constraint that the attitude angle should be constant before separation.A three-stage launch vehicle example was demonstrated.Comparing the AEM,GEM and SEM simulation results,the feasibility of the SEM guidance is verified.