The unique avionics design features of the Space Shuttle ascent flight control are described, along with the test article, test equipment, and test techniques used to verify the ascent flight control prior to commitment to the first orbital flight test. The ascent mission profiles are described, noting that upon ignition of the solid rocket boosters the Shuttle vehicle will rise vertically until achieving tower clearance. The Space Shuttle vehicle uses an integrated avionics system with the Orbiter avionics providing the command, control, and monitoring for the total mated Shuttle vehicle. The sensors and the actuator systems are discussed; the method of ascent flight control system verification is described, and it is concluded that the need for an advanced avionics integration and verification laboratory was recognized early in the program to provide maximum support to all program requirements.
Verification of the Space Shuttle ascent flight control
Automatic control in space ; 1979 ; Oxford
1980-01-01
Sonstige
Keine Angabe
Englisch
The Space Shuttle ascent flight control system
AIAA | 1976
|Space Shuttle Atmospheric ascent flight dynamics
NTRS | 1972
|Space shuttle ascent flight turbulence response
NTRS | 1972
Space Shuttle Ascent Flight Turbulence Response
NTIS | 1972
Tema Archiv | 1989
|