METHOD TO SUPPRESS LATERAL OSCILLATIONS OF MANEUVERABLE AIRCRAFT AT LARGE ANGLES OF ATTACK Russian patent published in 2010 - IPC B64C19/00 

FIELD: transport.

SUBSTANCE: proposed method comprises measuring mean angle of differential tail unit deflection, yaw angle, angle of attack, angular speeds of yaw and bank and generating control signals for rudder deflection, that of ailerons and tail unit deflection. Control algorithm for differential tail unit deflection is produced by selecting transfer coefficients according to relationships of K_ωx(φ_tu), K_ωy(φ_tu) and K_β(φ_tu) deviation from mean angle of tail unit deflection in the range of φ_tu=-30°…+10°. Said algorithm is adjusted for prevailing tail unit efficiency by its mean angle of deflection as follows: Δφ_tu=K_ωx.(ω_tu)ωx+K_ωy(φ_tu)ω_y+K_β(φ_tu)β, where Δφ_tu is tail unit differential deflection; K_ωx(φ_tu), K_ωy(φ_tu) and Kβ(φ_tu) are transfer coefficients of feedback in dependence upon mean angle of tail unit deflection; ω_x is angular speed of ban; ω_y is angular speed of yaw; β is yaw angle.

EFFECT: higher stability and controllability at major angles of attack α>30° at whatever mean angle of tail unit deflection.

2 cl, 7 dwg