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A MATLAB Script for Optimal Single Impulse De-orbit from Earth Orbits

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A MATLAB Script for Optimal Single Impulse De-orbit from Earth Orbits

by David Eagle

 

05 Nov 2012 (Updated 22 Jul 2013)

optimal impulsive maneuver required to de-orbit a spacecraft in a circular or elliptical Earth orbit

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Description

This document describes a MATLAB script named deorbit_snopt that can be used to compute the 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 geodetic altitude and relative flight path angle targets at the entry interface (EI).

MATLAB release MATLAB 7.14 (R2012a)
Other requirements Theis script uses the SNOPT nonlinear programming algorithm to solve this orbital mechanics problem. MATLAB versions of SNOPT can be found at Professor Philip Gill’s web site which is located at http://scicomp.ucsd.edu/~peg/.
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aerospace, mathematics, optimization, trajectory optimization
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Updates
22 Jul 2013

Added three-dimensional graphics display of the initial orbit and de-orbit trajectory. Updated PDF document.

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