Ballistic Interplanetary Trajectory Optimization - OTB

Optimization Toolbox version of a MATLAB script that solves the two impulse, patched-conic interplanetary trajectory problem.

https://sourceforge.net/u/cdeaglejr/profile/

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This submission is a MATLAB script called ipto_otb that can be used to design and optimize “patched conic” ballistic interplanetary trajectories between any two planets of our solar system. A patched-conic trajectory ignores the gravitational effect of both the departure and arrivals planets on the heliocentric orbital transfer trajectory (also called a zero sphere of influence trajectory (ZSOI)). This technique involves the solution of Lambert's problem relative to the Sun. The ipto_otb script also includes the option to include user-defined mission constraints such as departure energy, time-of-flight, and so forth during the trajectory optimization.
The ipto_otb MATLAB script also performs a graphical primer vector analysis of the two-impulse solution. This program feature displays the behavior of the primer vector magnitude and primer derivative magnitude as a function of mission elapsed time in days from departure. If the primer analysis indicates the solution can be improved with a third impulsive maneuver, the script will offer to optimize the two-impulse solution with an additional maneuver.
This MATLAB script reads a JPL planetary ephemerides in a machine-independent binary format (kernels) which are available from the JPL SPICE web site. These *.bsp ephemeris files are IEEE-Little Endian style of binary kernel. This is the binary form native to PC/Linux, PC/Windows and MAC/Intel machines. Ephemeris and other required data files, platform dependent versions of the MICE mex file and other functions are available at naif.jpl.nasa.gov/naif/toolkit_MATLAB.html. MICE is a MATLAB implementation of the JPL SPICE software system.
This ipto_otb script uses the fmincon nonlinear programming (NLP) algorithm from the MathWorks® Optimization Toolbox to solve this classic orbital mechanics problem.
This submission includes a Windows 64bit version of the MICE mex file.

Zitieren als

David Eagle (2026). Ballistic Interplanetary Trajectory Optimization - OTB (https://de.mathworks.com/matlabcentral/fileexchange/73513-ballistic-interplanetary-trajectory-optimization-otb), MATLAB Central File Exchange. Abgerufen .

Allgemeine Informationen

Kompatibilität der MATLAB-Version

  • Kompatibel mit R2019b

Plattform-Kompatibilität

  • Windows
  • macOS
  • Linux
Version Veröffentlicht Versionshinweise Action
1.7.0

Added option to include a Deep Space Maneuver (DSM)

1.6.0

Updated several algorithms, graphics displays and PDF documentation.

1.5.0

Changed fmincon algorithm to interior-point. Updated several MATLAB functions and PDF documentation.

1.4.0

Minor tweaks to the MATLAB source code, graphics updates and updated PDF user's guide.

1.3.0

Bug fix for comet/asteroid bodies

1.2.0

DE421 ephemeris

1.1.0

Updated to use the DE440s JPL ephemeris and MICE routines

1.0.0