基于阻力加速度倒数走廊的待飞航程解析预测方法  

Analytic Prediction Algorithm of the Range-to-Go on Drag Acceleration Reciprocal Corridor

作　　者：黄汉斌 杨业[1,2] 梁禄扬 Huang Hanbin;Yang Ye;Liang Luyang(Beijing Aerospace Automatic Control Institute,Beijing 100854 ,China;National Key Laboratory of Science and Technology on Aerospace Intelligence Control,Beijing 100854,China)

机构地区：[1]北京航天自动控制研究所,北京100854 [2]宇航智能控制技术国家级重点实验室,北京100854

出　　处：《航天控制》2019年第2期25-29,共5页Aerospace Control

摘　　要：针对再入段待飞航程估计问题,提出了一种简单解析积分的方法。本文将飞行过程约束和平衡滑翔约束转化为阻力加速度倒数走廊约束,利用三次样条函数描述阻力加速度倒数走廊,然后根据简化航程计算公式,推导出解析积分公式,从而得到待飞航程的解析解,进而设计阻力加速度剖面。仿真结果表明,本文提出的待飞航程计算方法效率高,可以实现与龙格库塔积分相同的精度;利用本文提出的方法,可以实现阻力加速度剖面的解析设计。Regarding the range-to-go’s prediction problem of re-entry flight,a simple analytic integral method is proposed. The path constraints and the quasi equilibrium glide condition( QEGC) are transformed into the constraints of drag acceleration reciprocal corridor. The drag acceleration reciprocal corridor can be described by the cubic spline function. According to the integral formula for calculating the range-to-go and the analytic corridor,the analytic formula for calculating the range-to-go can be derived. Then,the drag acceleration profile is designed. The simulation results show that the prediction algorithm for the range-to-go is simple and efficient,which has the same precision as the Runge-Kutta integral calculation,and the drag acceleration profile can be designed analytically.

关 键 词：升力式再入飞行器 阻力加速度倒数 三次样条 解析预测航程 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]