Impulsive Deboost for Maximum and Minimum Atmospheric Entry Angles
Keywords: Elliptic Orbits, Rocket Vehicles
AbstractDeboost 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.
How to Cite
Srivastava, T., & Nagpal, O. (2014). Impulsive Deboost for Maximum and Minimum Atmospheric Entry Angles. Defence Science Journal, 21(1), 27-30. https://doi.org/10.14429/dsj.21.6223
Copyright (c) 2016 Defence Science Journal
where otherwise noted, the Articles on this site are licensed under Creative Commons License: CC Attribution-Noncommercial-No Derivative Works 2.5 India