亚轨道飞行器航程控制的末端能量管理方法  

Terminal Area Energy Management of Suborbital Vehicle Based on Range Control

作　　者：王耀[1] 李文皓[1] 张珩[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《飞行力学》2009年第5期59-62,共4页Flight Dynamics

摘　　要：提出一种针对小能量亚轨道飞行器在无动力返回末端区域的多参数耦合、能量航向分离控制、动势能匹配衰减的精确控制的末端能量管理方法。以动能、势能作为约束条件,以航程作为优化指标,采用能量控制方法实时生成能量剖面,根据飞行器名义能量/航程在能量剖面中的位置确定迎角,最终生成三个姿态角。仿真结果表明用这种方法得到了良好的制导结果。A new terminal area energy management method is proposed for the suborbital vehicle which adopts many parameters;energy and azimuth for it are controlled separately,kinetic energy and potential energy decrease matched.The energy control method based on energy profile gets angle of attack by position of the energy/range what takes the kinetic energy and potential energy as restriction,and takes the range as optimization.Then it gives three attitude angles.The simulation tests for the TAEM show that this method mentioned above gets good guidance result.

关 键 词：亚轨道飞行器 末端能量管理 航程优化 能量剖面 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]