| 引用本文: | 吴楠,王锋,赵敏,等.高超声速滑翔再入飞行器的可达区快速预测.[J].国防科技大学学报,2021,43(1):1-6.[点击复制] |
| WU Nan,WANG Feng,ZHAO Min,et al.Fast prediction for footprint of hypersonic glide reentry vehicle[J].Journal of National University of Defense Technology,2021,43(1):1-6[点击复制] |
|
| |
|
|
| 本文已被：浏览 8097次 下载 6169次 |
| 高超声速滑翔再入飞行器的可达区快速预测 |
| 吴楠1,王锋1,赵敏2,孟凡坤1 |
|
(1. 中国人民解放军战略支援部队信息工程大学 数据与目标工程学院, 河南 郑州 450001;2. 中国人民解放军9589;4.部队, 北京 102211)
|
| 摘要: |
| 防御方对来袭滑翔再入飞行器进行可达区的预测存在先验信息量不足且时效性要求高等难题。为此提出一种基于最优化飞行假设的可达区快速预测方法:仅需已知目标当前位置、速度与最大升阻比(可基于雷达探测数据通过实时弹道估计获得),基于平衡滑翔假设和最大横程的埃格斯解分别获得目标最大纵程和横程终点坐标,在经纬度二维平面内,可达区即可近似为以两个最大横程终点间线段为短轴、最大纵程终点到短轴距离为半长轴的半椭圆区域。仿真结果表明,与传统的数值优化方法和常倾侧角方法相比,提出的方法具有利用先验信息少、精度较高和运算量小的优点,可满足实时性要求。 |
| 关键词: 可达区 高超声速滑翔再入飞行器 平衡滑翔 最大升阻比 |
| DOI：10.11887/j.cn.202101001 |
| 投稿日期：2019-06-18 |
| 基金项目:国家自然科学基金资助项目(41240031) |
|
| Fast prediction for footprint of hypersonic glide reentry vehicle |
| WU Nan1, WANG Feng1, ZHAO Min2, MENG Fankun1 |
|
(1. College of Data and Target Engineering, PLA Strategic Support Force Information Engineering University, Zhengzhou 450001, China;2. The PLA Unit 95894, Beijing 102211, China)
|
| Abstract: |
| Prediction for footprint of incoming hypersonic glide reentry vehicle as a defensive party has such problems as insufficient prior information and high timeliness requirement for solution. A fast prediction method of footprint based on optimal flight hypothesis was proposed:only if the position, velocity and maximum lift-drag ratio of the target at the current time are known (which can be obtained by real-time trajectory estimation based on radar detection data), based on the equilibrium glide hypothesis and the Egers solution of the maximum cross range, the coordinates of the maximum longitudinal range and cross range end points can be obtained respectively; then in the two-dimensional plane of longitude and latitude, the footprint can be approximated as a semi-elliptic area with the intersection of the two maximum cross range end points as the short axis and the distance from the maximum longitudinal range end point to the short axis as the half-long axis. The simulation results show that, compared with the traditional numerical optimization method and the constant bank angle method, the proposed method has the advantages of less prior information, higher accuracy and less computation, and can meet the real-time requirements. |
| Keywords: footprint hypersonic glide reentry vehicle equilibrium glide maximum lift-drag ratio |
|
|
|
|
|
