作　　者： (张阳）; (卜奎晨）; (王新民）; (李富贵）; (李滨）;

机构地区： 西北工业大学自动化学院,西安710129 中国运载火箭技术研究院,北京100076

出　　处： 《航天控制》 2017年第4期67-72,共6页

摘　　要： 提出了一种全程大气层内助推-滑翔弹道优化设计方法,通过在助推段进行弹道快速压低的方式,将助推-滑翔式飞行器的弹道顶点控制在大气层内,为实现空气舵稳定控制提供了条件;中段采用最佳升阻比攻角进行滑翔,以实现最大滑翔射程;引入比例导引计算指令过载和高度控制指令过载的比较,实现末制导弹道的平滑衔接,有利于导引头捕获跟踪目标及下压垂直对目标进行攻击。 A method for the optimization of gliding trajectory during whole journey in the atmosphere is depressing trajectory rapidly in the boosting section, the ballistic vertex of the booster-gliding aircraft is controlled in the atmosphere, so that conditions are provided for the stability con- trol by air rudders. Optimum angle of attack is used in the middle of the trajectory section to achieve the maximum gliding range. By comparing overload of proportional navigation instructions with overload of height control instructions, smooth convergence from midcourse trajectory to final guide trajectory is ac- quired, which is in favor of tracking target seeker capture and pressing down to attack the target vertically.

关 键 词： 高超声速飞行器 滑翔弹道 弹道优化 再入制导