| 引用本文: | 张大元,雷虎民,邵雷,等.临近空间高超声速目标拦截弹弹道规划.[J].国防科技大学学报,2015,37(3):91-96.[点击复制] |
| ZHANG Dayuan,LEI Humin,SHAO Lei,et al.Interceptor trajectory programming for near space hypersonic target[J].Journal of National University of Defense Technology,2015,37(3):91-96[点击复制] |
|
| |
|
|
| 本文已被：浏览 12488次 下载 7954次 |
| 临近空间高超声速目标拦截弹弹道规划 |
| 张大元1, 雷虎民1, 邵雷1, 李炯1, 肖增博2 |
|
(1.空军工程大学 防空反导学院，陕西 西安 710051;2.中国人民解放军93507部队,河北 石家庄 050200)
|
| 摘要: |
| 利用弹道规划设计了针对临近空间高超声速飞行器的拦截弹道。分析了临近空间高超声速目标拦截问题，将其定性为临近空间的远程高超声速拦截，并提出弹道规划需求；设计了一种两级助推的拦截弹，建立了考虑地球曲率和自转的拦截弹质点平面运动模型；根据弹道规划需求设计弹道约束，以末速最大、与终点距离误差最小和全程热量最小为指标建立拦截弹弹道规划问题；采用粒子群算法求解弹道，结果表明：符合约束的规划弹道是高抛再入形式，与比例导引弹道和准最佳弹道相比，拦截弹大部分时间飞行在大气层外，有效降低了气动热效应影响和对弹体材料的性能需求，且为末制导段提供良好的初始工作环境。 |
| 关键词: 临近空间 高超声速飞行器 粒子群算法 弹道规划 |
| DOI：10.11887/j.cn.201503015 |
| 投稿日期：2014-09-24 |
| 基金项目:航空科学基金资助项目（20120196003，20130196004） |
|
| Interceptor trajectory programming for near space hypersonic target |
| ZHANG Dayuan1, LEI Humin1, SHAO Lei1, LI Jiong1, XIAO Zengbo2 |
|
(1. Air and Missile Defense College, Air Force Engineering University, Xi′an 710051, China;2.The PLA Unit 93507, Shijiazhuang 050200, China)
|
| Abstract: |
| The trajectory of intercept hypersonic vehicle in Near Space was designed with trajectory programming method. The problem of intercepting the hypersonic vehicle in near space was analyzed and defined as long-range hypersonic intercept problem in near space, and the requirements for trajectory programming were proposed. A two-stage boost engine interceptor was designed, and the interceptor mass point model of plane motion was built in considering the earth curvature and rotation. And then, according to the requirements of trajectory programming, the trajectory restraint was designed. And the trajectory problem was established with such indexes, they were maximum terminal velocity, minimum distance error to the final point and minimum whole heat quantity. Particle swarm optimization algorithm was used to solve the problem. Results show that the programmed trajectory is a lofted trajectory which can fly out of atmosphere and reenter into it. When comparing with the proportion navigation trajectory and the near optimal trajectory, the missile will fly outside of atmospheric for most time, which can reduce the aerodynamic heat effects and cut down the requirements for the material, and provide a better initial operation environment for the terminal guidance phase. |
| Keywords: near space hypersonic vehicle particle swarm optimization algorithm trajectory programming |
|
|
|
|
|
