초록 ▼

An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer

An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer when, simultaneously, the turn command applied by the pilot to the elevational control surfaces (6G, 6D) exceeds a threshold and the measurement of the vertical acceleration of the aircraft exceeds a threshold.

대표청구항 ▼

[ What we claim is:] [1.] An aircraft comprising:a main wing structure (3G, 3D),elevation control aerodynamic surfaces (6G, 6D) controlled by a deliberate-actuation member (11) which is available to the pilot and which generators a turn command dm for said elevation-control aerodynamic surfaces (6G,

[ What we claim is:] [1.] An aircraft comprising:a main wing structure (3G, 3D),elevation control aerodynamic surfaces (6G, 6D) controlled by a deliberate-actuation member (11) which is available to the pilot and which generators a turn command dm for said elevation-control aerodynamic surfaces (6G, 6D), anda front stabilizer (5G, 5D), the planes of which are partially or completely adjustable, in coupled fashion, in terms of angular orientation under the action of actuators (10G, 10D) controlled by calculation means (14), rein said calculation means (14):continuously receive:said turn command dm generated by said deliberate-actuation member (11),a measurement of the angle of incidence .alpha.c of said front stabilizer (5G, 5D),a measurement of the Mach number M of said aircraft,a measurement of the flight altitude Zp of said aircraft, anda measurement of the vertical acceleration nz of said aircraft;hold in memory:a "nose-up" threshold dms for said turn command dm generated by said deliberate-actuation member (11),the aerodynamic characteristics (CA) of said front stabilizer (5G, 5D), anda first threshold nz1 for the measurement of the vertical acceleration nz of said aircraft;calculate, for said front stabilizer (5G, 5D), a turn command dic corresponding to an increase in the lift of this stabilizer when, simultaneously, said turn command dm generated by said actuating member exceeds said nose-up threshold dms and the measurement of the vertical acceleration nz of said aircraft exceeds said first threshold nz1; andapply said turn command dic thus calculated to said front stabilizer (5G, 5D) via said actuators (10G, 10D).