摘要
以未来火星探测任务为背景,简要分析了通过气动刹车到达目标轨道方案的优缺点。基于给定的火星大气修正指数模型,建立了气动刹车的动力学模型。针对飞行器自身和轨道限制,设置必要的约束条件,利用高斯伪谱法求解出气动刹车方案中每个周期所需的维持近火点高度的脉冲速度增量,实现了通过气动刹车的方式到达指定轨道的目标。结果表明,利用高斯伪谱法优化计算得到的气动刹车方案可以满足要求,可为气动刹车相关的后续研究提供新的思路。
Based on the background of future Mars exploration, merits and demerits of the trajectory transfer method of aerobraking are discussed. An improved exponential Martian atmospheric model is chosen. Then a dynamic model of aerobraking is established. Con- straint conditions are set according to the restrictions of the spacecraft and the orbit. Change in velocity of each circle of aerobraking to maintain the altitude of the periapsis is obtained by GPOPS. Thus, the goal of entering the target orbit by using aerobraking method is achieved. The results indicate that the scheme of aerobraking obtained by the optimal calcu- lation of GPOPS is available and it provides a new way for future study of aerobraking.
出处
《现代应用物理》
2016年第3期58-62,共5页
Modern Applied Physics
基金
国家自然科学基金资助项目(11372345)
关键词
火星探测
高斯伪谱法
轨道仿真
气动刹车
Mars exploration
Gauss pseudospectral method
trajectory simulation
aerobraking
