This paper describes a variable-gain optimal discrete output-feedback design approach that is applied to a nonlinear flight regime covering a wide angle-of-attack range that includes stall and poststall. The paper includes brief descriptions of the variable-gain formulation, the discrete-control structure and flight equations used to apply the design approach, and the high performance airplane model used in the application. Both linear and nonlinear analyses are shown for a longitudinal four-model design case with angles of attack of 5, 15, 35, and 60 deg.
Application of variable-gain output feedback for high-alpha control
AIAA Guidance, Navigation and Control Conference ; 1989 ; Boston, MA, United States
1989-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
A variable-gain output feedback control design approach
NTRS | 1989
|A variable-gain output feedback control design approach
AIAA | 1989
|