On the high eccentricity aerobraking orbit transfer problem, with parametric analysis and numerical study.

摘要

This thesis presents the results of a numerical examination of initial perigee aerobraking from 80 km to 100 km with or without a plane-change. Each apogee decay without maneuver except at the final apogee has a {dollar}Delta{dollar}V for target plane-change. The feasibility and practicability of employing a highly elliptical orbit aerobraking at the perigee for return of the reuseable vehicle or satellite from HEO (High Earth Orbit) were investigated.; The comparison between in plane aerobraking and Hohmann transfer with two impulses is included, the output data shows multipass aerobraking as a way to save more energy and time than traditional Hohmann transfer to arrive at the final orbit.; The parametric analysis for orbital elements examines the effects of varying gravity harmonic coefficients and parameters in the density models on the reentry trajectory. Earth gravity model is simplified under suitable assumptions in this thesis. Pre-analysis provides essential input for navigation, guidance and controller design. A comparison is made using the POHOP simulation program to preform an aerobraking study in the perigee corridor range of 80 to 100 km.