摘要
在充分调研国内外轨迹优化方法的基础上,针对可重复使用助推飞行器飞行过程中有一段大攻角飞行且期间还需进行一次大角度翻转的飞行模式,以俯仰角为最优控制量,采用直接打靶法和序列二次规划法,选择速度作为过渡量,将分离点至再入结束点的飞行过程分为调姿转弯段和再入段进行优化.分析了过渡速度和分离点处弹道倾角的取值,得到了较为合理的过渡速度和分离点处弹道倾角的取值范围,进行了该飞行过程的全段轨迹优化.仿真结果表明本文给出的优化策略能较好地获得一条满足约束条件的优化轨迹.
On the basis of review of trajectory optimization method at home and abroad,a method that attitude-adjusting return phase and reentry phase were optimized separately was proposed aiming at Reusable Booster Vehicle（RBV） flying with large angle of attack and a wide-angle return.The direct shooting method and sequential quadratic programming algorithm were used to solve the optimization problem.The pitch angle was taken as optimal control quantity.Transition speed and path angle were analyzed,and the optimal transition speed and path angle were obtained.The whole trajectory from separation point to the end point of reentry of reusable booster vehicle was optimized,and the optimal trajectory was obtained.Simulation results show that an optimal trajectory which satisfies trajectory constraints well can be obtained by the optimization strategy.
出处
《弹道学报》
EI
CSCD
北大核心
2011年第4期5-9,共5页
Journal of Ballistics
关键词
可重复使用飞行器
直接打靶法
序列二次规划
轨迹优化
reusable vehicle
direct shooting method
sequential quadratic programming
trajectory optimization
