Path: LunarMissions/LunarLanding
% Compare the state transition matrix to numerical integration The first test compares the state propagation to the numerical integration in a circular orbit. The second test compares a simulation with a constant thrust. This applies a constant thrust to slow the orbital velocity causing the lander to descend. This script runs the nonlinear simulation and then compares the results with the state transition matrix approach that will be used in the optimizer. See also: PropagateState3D, RHSPlanet3D, RHSPlanet3DToAB % -------------------------------------------------------------------------- Copyright (c) 2015 Princeton Satellite Systems, Inc. All rights reserved. -------------------------------------------------------------------------- Since 2016.1 --------------------------------------------------------------------------