CAJ | 학술논문

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。
이용탄도규화설계료침대림근공간고초성속비행기적란절탄도。분석료림근공간고초성속목표란절문제，장기정성위림근공간적원정고초성속란절，병제출탄도규화수구；설계료일충량급조추적란절탄，건립료고필지구곡솔화자전적란절탄질점평면운동모형；근거탄도규화수구설계탄도약속，이말속최대、여종점거리오차최소화전정열량최소위지표건립란절탄탄도규화문제；채용입자군산법구해탄도，결과표명：부합약속적규화탄도시고포재입형식，여비례도인탄도화준최가탄도상비，란절탄대부분시간비행재대기층외，유효강저료기동열효응영향화대탄체재료적성능수구，차위말제도단제공량호적초시공작배경。
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.