The minor loop and minor loop support modules which maintain correct vehicle attitude control by generating vehicle attitude error signals were verified. The logic is checked during boost and orbit (unusual timing situations necessitate the additional orbit checks) and the constants used by these modules checked at every point during the flight. Since the same logic instructions are used throughout the flight with only the constants changing, verification of the logic at two points and the constants at all points verify the logic throughout the flight.
Launch vehicle attitude control
1975-04-15
Miscellaneous
No indication
English
Adaptive Attitude Control of the Crew Launch Vehicle
NTRS | 2010
|Adaptive Attitude Control of the Crew Launch Vehicle
NTIS | 2010
|NOVEL ATTITUDE CONTROL DESIGN OF SPACE LAUNCH VEHICLE
TIBKAT | 2021
|Orion Launch Abort Vehicle Attitude Control Motor Testing
British Library Conference Proceedings | 2011
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