摘要
针对滑翔式高超声速飞行器(HGV)平衡滑翔轨迹可达区域的高精度快速计算问题,研究了一种基于降阶动力学模型和连续凸优化方法的可达区域计算方法;首先,根据"准平衡滑翔假设"条件,将再入飞行器三自由度动力学方程进行降阶处理,得到以速度为自变量的三阶动力学方程;然后,将可达区域计算问题描述为一系列满足再入走廊约束和初、末状态约束下的横程最大优化问题,将动力学方程进行线性化、离散化处理后,采用连续凸优化方法对该问题进行求解,得到了滑翔飞行器不同末端速度下的可达区域;最后,以CAV-H飞行器模型为例进行了仿真验证,结果表明,该方法具有较高的求解效率和可达区域计算精度。
A method based on reduced-order dynamic model and sequential convex optimization is studied for the high precision and efficient calculation of hypersonic gliding vehicle’s equilibrium gliding trajectory footprint.Firstly,according to the quasi-equilibrium gliding hypothesis,the dynamic equation of reentry vehicle is simplified to obtain the third-order dynamic equation with velocity as independent variable.Then,the footprint calculation problem is described as a series of maximal cross-range optimization problems satisfying reentry corridor constraints and initial and final state constraints.After linearization and discretization of the simplified dynamic equations,the problem is solved by the continuous convex optimization method,and the footprint of the vehicle at different terminal speeds is obtained.Finally,the CAV-H model is taken as an example to verify the simulation.The results show that the proposed method has high efficiency and high accuracy in the footprint calculation.
作者
樊朋飞
郭云鹤
凡永华
闫杰
Fan Pengfei;Guo Yunhe;Fan Yonghua;Yan Jie(College of Astronautics, Northwestern Polytechnical University,Xi’an710072, China;Shanghai Electro-Mechanical Engineering Institute,Shanghai201109, China)
出处
《计算机测量与控制》
2019年第5期136-140,共5页
Computer Measurement &Control
关键词
高超声速滑翔飞行器
平衡滑翔
可达区域计算
连续凸优化方法
hypersonic gliding vehicle
equilibrium gliding
footprint calculation
sequential convex optimization
