临近空间高超声速目标拦截弹弹道规划

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。

Interceptor trajectory programming for near space hypersonic target

The trajectory to intercept hypersonic vehicle in Near Space is 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, requirements for trajectory programming was proposed, too. A interceptor with two stage boost engines was designed, and its mass model in the trajectory plane was built considering the Earth as spherical and rotating. And then, a programming problem was established with requirements got above as limitation, whose indexes were maximum terminal velocity, minimum distance to the final point and minimum whole heat quantity. Particle swarm optimization method was used to solve the problem, and the proportion navigation trajectory and the near optimal trajectory were calculated as comparisons. Results show that, the programmed trajectory is a lofted trajectory which can fly out of atmosphere and reenter into it, the missile will fly outside of atmospheric for most time, which can reduce effects caused by aero-thermal and cut down requirements for the material, and provide a better initial operation environment for the terminal guidance.