Gravity-assist Trajectory Optimization - OTB version

A MATLAB Script for Interplanetary Patched-Conic, Single Gravity-Assist Trajectory Design, Analysis and Optimization

This submission is a MATLAB script named flyby_otb that can be used to optimize interplanetary, patched-conic trajectories that include a zero sphere of influence (ZSOI) single gravity assist maneuver. The user specifies the departure, flyby and arrival planets along with initial guesses for the departure, flyby and arrival calendar dates, and lower and upper bounds for the flyby altitude. This script searches for a patched-conic, gravity-assist trajectory that satisfies the flyby mission constraints (V-infinity matching and bounded flyby altitude) and minimizes the departure, arrival or total impulsive heliocentric delta-v for the mission. The type of trajectory optimization is specified by the user.

This MATLAB script reads JPL lunar and solar ephemerides in a machine-independent binary format (kernels) which are available from the SPICE web site and by anonymous ftp from ftp://ssd.jpl.nasa.gov/pub/eph/planets/bsp. 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. Additional information about JPL ephemerides can be found at http://naif.jpl.nasa.gov/naif/.

The flyby_otb script uses routines from the MICE software suite to read and evaluate the JPL ephemeris file. Platform-specific MICE mex files, support functions and binary ephemeris files are available at naif.jpl.nasa.gov/naif/toolkit_MATLAB.html. MICE is a MATLAB implementation of the SPICE library created by JPL.

The software provides a simple two-dimensional graphic display of the heliocentric planet orbits and the interplanetary transfer trajectory. It also provides a three-dimensional graphic display of the flyby trajectory relative to the gravity-assist planet along with the corresponding classical orbital elements.