Module rocket_landing 

Rocket Powered Landing trajectory optimization.

Implements fuel-optimal powered descent guidance using convex optimization, inspired by the lossless convexification approach to rocket landing.

Problem formulation (2D)

• State: [x, y, vx, vy] (position and velocity)
• Control: [Tx, Ty] (thrust vector components)
• Dynamics: double integrator with gravity
  • x_dot = vx, y_dot = vy
  • vx_dot = Tx / m, vy_dot = Ty / m - g
• Constraints: |T| <= T_max (second-order cone constraint on thrust magnitude)
• Terminal: land at target position with zero velocity
• Objective: minimize total thrust (fuel proxy)

Structs

LandingTarget

Target landing condition.

RocketLandingConfig

Configuration for the rocket landing problem.

RocketState

Initial condition for the rocket.

RocketTrajectory

Result of the trajectory optimization.

Functions

simulate_freefall

Simulate free-fall trajectory (no thrust) for comparison.

solve_landing_trajectory

Solve the rocket powered landing trajectory optimization problem.