Impulsive Deboost for Maximum and Minimum Atmospheric Entry Angles

Abstract

Deboost of rocket vehicles initially moving in elliptic orbits for maximum and minimum atmospheric entry is analysed. It is shown that in general with specified retrofire velocity impulse and entry altitude, maximum entry angle is obtained when impulse is applied tangentially at the apogee whereas entry angle occurs when retrofire impulse is applied tangentially at the perigee. Existence conditions for only maximum or minimum or both neither maximum nor minimum entry have also been investigated.