The impact of independent canard and flaperon control of the longitudinal axis of a generic forward swept wing aircraft is examined. The Linear Quadratic Gaussian (LQG)/Loop Transfer Recovery (LTR) method is used to design three compensators: two single-input-single-output (SISO) systems, one with angle of attack as output and canard as control, the other with pitch attitude as output and canard as control, and a two-input-two-output system with both canard and flaperon controlling both the pitch attitude and angle of attack. The performances of the three systems are compared showing the addition of flaperon control allows the aircraft to perform in the precision control modes with very little loss of command following accuracy.
Multivariable control of a forward swept wing aircraft
1986-01-01
Theses
No indication
English
High Performance Forward Swept Wing Aircraft
NTIS | 1986
|High performance forward swept wing aircraft
NTRS | 1988
|Dynamics and control of forward swept wing aircraft
NTRS | 1983
|Aircraft Having Variable Incidence Forward-Swept Wing
NTIS | 1981
|