摘要
针对重复使用运载器原场返回这一发展思路存在的诸多问题,提出一种在发动机二次点火方案下结合逆向积分的原场返回轨迹设计方法。该方法将原场返回分为轨迹回转段与再入返回段两部分进行设计。前者通过姿态调整、速度调整实现飞行方向朝向发射场;后者通过逆向积分设计再入返回轨迹,并进一步确定轨迹回转段的终端需求。仿真结果表明,该设计方法能够在满足约束条件下获得原场返回的完整飞行轨迹。
In order to tackle the problems within returning to launch site method for reusable launch vehicle,trajectory design method was proposed based on secondary ignition and backward integration.The process was divided into trajectory rotation phase and re-entry phase.Flight direction was reversed to launch site along with attitude and velocity adjustment in the first phase,then reentry trajectory and requests for the first phase were given by the second phase using backward integration.Numerical simulations results show that whole returning to launch site trajectory meeting constraints could be acquired using the proposed method.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2017年第1期110-114,共5页
Journal of Solid Rocket Technology
基金
国家863项目(2014AA7021004)
关键词
重复使用运载器
原场返回
二次点火
逆向积分
reusable launch vehicle
return to launch site
secondary ignition
backward integration
