The Orbiter entry guidance system controls the Space Shuttle Orbiter from the initial atmospheric penetration point to the point at which an earth relative velocity of 2500 feet/second is reached. At the latter point, control of the Orbiter is transferred to the terminal area energy management system. The entry guidance system is based on the concept that the range to be flown during entry is a unique function of the drag deceleration profile flown throughout the entry. The range prediction during entry is based on analytic equations which are simple drag deceleration functions of earth relative velocity above Mach 10.5 and energy with respect to the earth below Mach 10.5. Flight through the entry corridor is accomplished by linking these simple drag deceleration functions together in series in order to define a drag deceleration reference profile. The results of the first three Space Shuttle missions have not only verified the entry guidance concept but have also demonstrated the stability of the guidance system.
Atmospheric guidance techniques and performance
Guidance and Control Conference ; 1982 ; San Diego, CA
1982-01-01
Miscellaneous
No indication
English
Atmospheric guidance techniques and performance
AIAA | 1982
|Exo-Atmospheric Mid-Course Guidance
AIAA | 2015
|Doppler radars for guidance design techniques and performance
TIBKAT | 1959
|Four-dimensional guidance of atmospheric vehicles
AIAA | 1996
|Atmospheric Reentry Guidance of Manned Spacecraft
British Library Conference Proceedings | 1994
|