Code covered by the BSD License
- atan3 (a, b)
four quadrant inverse tangent
- deltav_guess(oev1, alttar...initial guess for de-orbit delta-v vector and flight time
- deorbit_shoot(x)
objective function and EI equality constraints
- eci2fpc1(gast, reci, veci)
convert inertial state vector to flight path coordinates
- eci2orb1 (mu, r, v)
convert eci state vector to six classical orbital
- gast1 (jdate)
Greenwich apparent sidereal time
- gdate (jdate)
convert Julian date to Gregorian (calendar) date
- geodet1 (rmag, dec)
geodetic latitude and altitude
- j2eqm (t, y)
first order equations of orbital motion
- jd2str(jdate)
convert Julian date to string equivalent
- julian (month, day, year)
Julian date
- keycheck
pause and request user input
- oeprint1(mu, oev)
print six classical orbital elements
- orb2eci(mu, oev)
convert classical orbital elements to eci state vector
- readdata(filename)
NOTE: all angular elements are returned in radians
- svprint(r, v)
print position and velocity vectors and magnitudes
- tof1(mu, sma, ecc, tanom1...time of flight between two true anomalies
- twobody2 (mu, tau, ri, vi)solve the two body initial value problem
- ueci2angles(reci, veci, u...convect eci unit vector to rtn angles
- deorbit_snopt.m
-
View all files
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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| File Information |
| 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)
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| 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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| Updates |
| 22 Jul 2013 |
Added three-dimensional graphics display of the initial orbit and de-orbit trajectory. Updated PDF document. |
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