中远程火箭被动段飞行参数的一种预示方法

A Predictable Method of the Flight Parameters for the Unpowered Phase of the Middle/Long Range Rocket

对中远程火箭 ,在地面冲量发射、椭圆弹道和最小能量弹道的假设条件下 ,再入段在“直线弹道”的假设条件下 ,对给定射程提出了一种预示再入飞行器被动段飞行参数的近似解析计算方法。再入飞行器被动段飞行参数包括 :被动段飞行时间 ;最大飞行高度 ;再入初始飞行速度与弹道倾角 ;最大轴向过载系数与最大动压及它们的发生高度 ;驻点最大外压、最大热流与总加热量 ;球头最大热流与总加热量 ;锥面最大外压、最大热流与总加热量 ;

This paper gives an approximate analytical calculation method which indicates the flight data of reentry vehicle in unpowered phase for a given range. This calculation is on the assumption that the middle/long range rocket is ground impulse fired, flying along a elliptic and minimum energy trajectory, and the reentry phase is a straight-line path. The flight data of reentry vehicle in unpowered phase include: fight time in unpowered phase; the maximum fight altitude; initial reentry velocity and trajectory inclination angle; the maximum axial overload coefficient,the maximum dynamic pressure and altitude at which the maximum axial overload and dynamic pressure occurs; the maximum exterior pressure, the maximum heat flow and total heating at stagnation point; the maximum heat flow and total heating of ball-head; maximum exterior pressure, maximum heat flow and total heating on conical surface; and reentry flight time,etc.