A guidance method for the space shuttle's transition from hypersonic entry to subsonic cruising flight is presented. The method evolves from a numerical trajectory optimization technique in which kinetic energy and total energy (per unit weight) replace velocity and time in the dynamic equations. This allows the open end-time problem to be transformed to one of fixed terminal energy. In its ultimate form, 'E-Guidance' obtains energy balance (including dynamic-pressure-rate damping) and path length control by angle-of-attack modulation and cross-range control by roll angle modulation. The guidance functions also form the basis for a pilot display of instantaneous maneuver limits and destination. Numerical results illustrate the E-Guidance concept and the optimal trajectories on which it is based.
Optimal guidance for the space shuttle transition.
International Astronautical Federation, International Astronautical Congress ; 1972 ; Vienna, Austria
1972-10-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Optimal guidance for the space shuttle transition
NTRS | 1974
|Optimal Guidance for the Space Shuttle Transition
AIAA | 2003
|Optimal Guidance for the Space Shuttle Transition
AIAA | 1974
|NTRS | 1970
|NTIS | 1970
|