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Optimal Single Impulse De-orbit from Earth Orbits - OTB

version 1.0.0 (624 KB) by David Eagle
Optimization Toolbox version of the deorbit.m MATLAB script which determines optimal de-orbit maneuvers.

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Updated 11 Dec 2019

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This document describes a MATLAB script named deorbit_otb that can be used to compute the single optimal impulsive maneuver required to de-orbit a spacecraft in a circular or elliptical Earth orbit. The user provides the classical orbital elements of the initial orbit along with the desired geodetic altitude and relative flight path angle targets at the entry interface (EI).

Cite As

David Eagle (2020). Optimal Single Impulse De-orbit from Earth Orbits - OTB (https://www.mathworks.com/matlabcentral/fileexchange/73645-optimal-single-impulse-de-orbit-from-earth-orbits-otb), MATLAB Central File Exchange. Retrieved .

Comments and Ratings (1)

Gatech AE

Have you considered using Gauss' method or p-Iteration for determining the delta-v? It wouldn't require the optimization toolbox to sweep through TOF for minimizing delta-v, and would give the ending velocity vector without ode45.

MATLAB Release Compatibility
Created with R2019b
Compatible with any release
Platform Compatibility
Windows macOS Linux