N-body, Single Gravity-Assist Trajectory Design - OTB

version 1.3.0 (16.2 MB) by David Eagle
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations

71 Downloads

Updated Mon, 08 Aug 2022 16:52:58 +0000

View License

MATLAB script named nbody_flyby_otb that can be used to design interplanetary n-body trajectories that include a single gravity assist maneuver. This script uses a patched-conic (zero sphere-of-influence, ZSOI) solution of the gravity-assist flyby problem as an initial guess for the n-body algorithm. The departure equations of motion include first-order Earth oblateness and point-mass gravity of the sun and moon. The n-body heliocentric equations of motion include the point-mass gravity of the first eight planets.
The n-body trajectory optimization algorithm allows the user to select a “targeting” option at the arrival planet from this list.
  • B-plane components (B dot T and B dot R)
  • orbital elements (periapsis radius and orbital inclination)
  • entry interface (flight path angle, altitude and inclination)
  • node/apse alignment (periapsis radius, ascending node and argument of periapsis)
The n-body simulation minimizes the scalar magnitude of an impulsive interplanetary trajectory correction maneuver (TCM) required to achieve these targets. This maneuver is performed at a user-defined delta time after the gravity-assist.

Cite As

David Eagle (2022). N-body, Single Gravity-Assist Trajectory Design - OTB (https://www.mathworks.com/matlabcentral/fileexchange/89137-n-body-single-gravity-assist-trajectory-design-otb), MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2020b
Compatible with any release
Platform Compatibility
Windows macOS Linux

Community Treasure Hunt

Find the treasures in MATLAB Central and discover how the community can help you!

Start Hunting!