Finite-burn circularization of an elliptical orbit - OTB

This script circularizes an initial elliptical orbit by performing a finite-burn maneuver at apogee of the initial elliptical orbit.

This script can be used to optimize a single finite-burn orbital maneuver that achieves circularization of an elliptical orbit. The simulation assumes the propulsive maneuver is continuous, co-planar and modeled as a series of optimal discretized steering angles. The script attempts to minimize the thrust duration of the finite-burn while solving for user-defined orbital boundary conditions at burnout such as perigee and/or apogee altitudes.

In this MATLAB script, the Keplerian orbital motion is modeled using modified equinoctial orbital elements and the scripts assume the thrust magnitude and specific impulse are constant during the entire orbit transfer maneuver. Information about modeling in this flight path system can be found in Appendix A, Trajectory Modeling and Targeting in the Modified Equinoctial Orbital Elements System of the included PDF user's manual.

The optimization of the maneuver steering angles in each script is performed using the fmincon nonlinear programming (NLP) algorithm. This implementation features the interior-point option.

This numerical method is part of the Mathworks® Optimization Toolbox.