Energy-Angular Momentum Closed-Loop Guidance Algorithm for Launch Vehicles

An improved method for launch vehicle guidance is disclosed. A pre-computed energy-angular momentum (E-J) curve to place a launch vehicle into a target orbit is received and stored. An energy, angular momentum, radial distance, velocity magnitude, and flight path angle of the launch vehicle are computed from state vector data while the launch vehicle is traveling to the target orbit. The pre-computed E-J curve and the computed energy, angular momentum, radial distance, velocity magnitude, and flight path angle of the launch vehicle are used to determine pitch and pitch rate of the launch vehicle.