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

version 1.2 (529 KB) by

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

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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).

Comments and Ratings (2)

vivek mainali

I have been running the submission using snopt matlab but it is showing the error "Undefined function or method 'snopt' for input arguments of type 'double'"
Undefined function or method 'julian' for input arguments of type 'double'.

Error in ==> readdata at 110
jdate0 = julian(month, day, year);

Error in ==> deorbit_snopt at 64
[fid, ta_lower, ta_upper] = readdata(filename);

Please help me out on the issue.
respond me at mainali.vivek001@gmail.com

dear David, I'sm a student of B.tech. aerospace and currently working on the topic optimal single impulse de-orbit from earth orbits. i've downloaded the submission of this topic by you but i'am having problem in running the codes in matlab. please help me out with this. my email id is mainali.vivek001@gmail.com

Updates

1.2

Added version of main script (deorbit_snopt_64bit) that uses the March 17, 2014 version of SNOPT.

1.1

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

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MATLAB 7.13 (R2011b)

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