
Accession Number : AD0678052
Title : OPTIMUM THREEDIMENSIONAL DEORBIT FOR SPECIFIC REENTRY ANGLE FROM ELLIPTICAL ORBITS,
Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF SYSTEMS ENGINEERING OPERATIONS
Personal Author(s) : Chu,S. T.
Report Date : AUG 1968
Pagination or Media Count : 65
Abstract : The minimum impulsive velocity requirements for threedimensional deorbit from elliptical orbits to achieve a specified reentry angle are analyzed. This analysis, representing an extension of a previous study of deorbit from circular orbits, considers two cases: the first case determines the optimum impulsive velocity for a given reentry angle and a given heading angle change; the second treats the problem of a given reentry angle and a given earthcentral crossrange angle. Significant variations of the minimum impulsive velocity requirement result when the specified position of deorbit changes between the apogee and the perigee. For the first case, the minimumimpulse solution results in both pure retro and oriented retro for deorbit from the perigee, depending upon the values specified for the plane change and the reentry angle. Deorbit from the apogee, on the other hand, always results in a pure retro solution for minimum impulse; deorbit from a general position in orbit always results in an oriented retro solution. A global optimum representing a minimum deorbit impulse by allowing variations in both the deorbit location and the orientation of the impulse is also studied. For the second case, the magnitudes of optimum impulsive velocity for constant values of crossrange angle are approximately equal to those of constant plane change of equivalent value. (Author)
Descriptors : (*DESCENT TRAJECTORIES, OPTIMIZATION), (*REENTRY VEHICLES, DESCENT TRAJECTORIES), ATMOSPHERE ENTRY, TRANSFER TRAJECTORIES, APOGEE, PERIGEE, ELLIPTICAL ORBIT TRAJECTORIES
Subject Categories : Spacecraft Trajectories and Reentry
Ground Support Sys & Facil For Space Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE