This paper examines feasibility and performance issues in using Control Moment Gyroscopes (CMGs) to control the attitude of a fixed-wing aircraft. The paper describes a control system structure that permits allocating control authority and bandwidth between a CMG system and conventional aerodynamic control surfaces to stabilize a vehicle with neutral aerodynamic stability. A simulation study explores the interplay between aerodynamic and CMG effects, and indicates desirable physical characteristics for a CMG system to be used for aircraft attitude control.
A Feasibility Study on the Control of a Generic Air Vehicle Using Control Moment Gyros
AIAA Guidance, Navigation, and Control Conference and Exhibit ; 2006 ; Keystone, CO, United States
2006-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
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