【作者】 董萌； 关英姿；

【Author】 DONG Meng;GUAN Ying-zi;Harbin Institute of Technology,Spacecraft System Simulation Laboratory;

【机构】 哈尔滨工业大学航天学院航天工程系；

【摘要】 为了解决RLV(可重复使用飞行器)的末端能量管理(TAEM)段飞行控制问题,本文进行了轨迹设计和制导策略研究。RLV在该段一直处于无动力飞行,且升阻比较小。文章首先对该飞行阶段的捕获段、航向校正段和预着陆段进行了轨迹设计,设计的关键在于地面剩余航程预测,主要利用搜索法改变航向校正圆柱的半径大小和圆心位置来调整能量航程比。TAEM段轨迹制导主要通过速度和高度两个通道来控制能量,一般分为侧向制导和纵向制导:侧向制导通过控制速度跟踪地面航迹,纵向制导则通过控制高度跟踪高度剖面。文章首先给出了各飞行阶段的地面剩余航程预测方法、高度剖面规划方法和轨迹可行性验证方法,接着根据各飞行阶段的飞行特点给出相应的制导指令,最后进行具体的仿真计算,并考虑常见的几项随机干扰进行了蒙特卡洛打靶分析。实验结果表明:制导结束后末端高度偏差为1.5m,速度偏差为8.42m/s,弹道倾角偏差为-0.145°,横向位移偏差为1.6m,同时满足动压小于20kpa、过载小于5的约束条件,设计的轨迹可行,制导精度也满足要求。更多还原

【Abstract】 Tosolve the flight-control problem of RLV(reusable spacecraft) during Terminal Area Energy Management(TAEM),this paper has studied the trajectory design and trajectory control strategy of it.RLV in this flight segment has been in non-powered flight and the lift-drag is relatively small.This article mainly designs the trajectory of acquisition,HAC turn and pre-final phases.The key of trajectory design is to forecast remaining ground voyage,using search method to change the radius of the cylinder size and the center position of it in order to achieve the purpose of adjusting the energy range ratio.TAEM trajectory guide primarily controls energy by two channels of speed and height,generally includes lateral and vertical guidance.The aim of lateral guidance is tracking ground track by controlling speed,meanwhile vertical guidance is to track height profile through controlling the height The article firstly gives the method of forecasting the remaining flight phases range on the ground,trajectory planning method and feasibility authentication method,according to the characteristics of each phase of flight gives the appropriate guidance commands.Finally a specific simulation is done.Taking several common random interferences into account,a Monte Carlo shooting analysis is also executed.The experimental results shows that:in the end of the guide,height deviation is 1.5m,the speed deviation is 8.42m/s,trajectory angle deviation is-0.145 deg,the lateral displacement deviation is 1.6m and the dynamic pressure meets the maximum dynamic pressure 20 kpa constraints.This trajectory design is feasible and guidance precision also meets the requirements.更多还原