pub fn solve_landing_trajectory(
initial: &RocketState,
target: &LandingTarget,
config: &RocketLandingConfig,
) -> Option<RocketTrajectory>Expand description
Solve the rocket powered landing trajectory optimization problem.
Uses a QP formulation with second-order cone constraints on thrust magnitude. The dynamics are discretized as a linear system (double integrator + gravity) and embedded as equality constraints.
Returns None if the solver fails to find a solution.