Dynamic guidance of orbiter gliders: alignment, final approach, and landing

new algorithm capable of guiding an orbiter glider to a target point with a prescribed alignment and descent path angle is presented. This algorithm can initiate Terminal Area Energy Management (TAEM) before reaching steady state and perform the Final Approach and Landing (FA L). During TAEM, runway alignment is done through a moving virtual target derived from steady state, while during FA L, a transient (or flare) is used to reach the extremely shallow descent path angles. All decisions are made dynamically relying solely on local information (position, speed, attitude, and atmospheric parameters), and all structural limits of the glider are respected at all times. As a proof of concept, a Space Shuttle return flight is simulated. For a large multitude of initial conditions and targets, the algorithm is able to consistently deliver distance errors below 19 m (transverse errors below 4 m), alignment errors below 1^∘ , descent path angles at the intended - 2^∘ , and vertical descent speeds below 8.5 m/s with control time intervals of 0.1 s.