Abstract: The present invention relates to a system for the yaw control of an aircraft fitted with a plurality of engines, the system (SC) comprising in particular a computation unit (16) formulating a command dr for yaw control, dr=Ka.&PHgr;c+Kb.p+Kc.&PHgr;+Kd.r+Ke.&bgr;, on the basis of the controlled roll attitude &PHgr;c, of the roll rate p, of the effective roll attitude &PHgr;, of the yaw rate r, of the sideslip &bgr; and of gains Ka, Kb, Kc, Kd and Ke which are fixed by a device (28). According to the invention, the system (SC) comprises a a device (30) for detecting any fault with an engine of the aircraft, and the device (28) is formed in such a way as to modify the values of the gains Ka, Kd and Ke relating respectively to the controlled roll attitude &PHgr;c, to the yaw rate r and to the sideslip &bgr;, upon the detection by the device (30) of a fault with an engine of the aircraft.

Abstract: A system for protecting an aircraft in cruising flight against excessive load factors when a vertical gust of wind occurs is disclosed. The system has a pitch-attitude flight control system (21) which is under the control of a pilot of the aircraft, an automatic pilot (26), a switch (25) allowing the aerodynamic pitch-attitude control surfaces (22) of the aircraft to be controlled either by the flight control system (21) or by the automatic pilot (26), and a protection system (31) capable of acting on the switch (25) to disconnect the automatic pilot (26) and switch on the flight control system (21). The disconnection of the automatic pilot (26) and the switching-on of the flight control system (21) is delayed by a delay time which is at least approximately equal to a typical duration of a vertical gust of wind, and the switching-on of the flight control system (21) is not carried out unless the gust of wind persists when the delay time has elapsed.

Abstract: An apparatus and method for detecting vertical gusts of wind on board an aircraft in cruising flight is disclosed. The method includes the steps of: calculating an absolute value (.vertline..alpha.-.theta..vertline.) of a difference between a pair of first differentials with respect to time (.alpha. and .theta.) of a current incidence .alpha. and a current pitch attitude .theta. of the aircraft, comparing the absolute value to an upper threshold (Ss), comparing a current Mach number (M) of the aircraft to a Mach number threshold (Mo), and generating an electrical signal that represents presence of a vertical gust of wind when the absolute value is above the upper threshold, when the current Mach number is above the Mach number threshold, and when aerodynamic flaps and slats of the aircraft are in a clean configuration.

Abstract: The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).

Abstract: A system for integrated pitch and thrust control of an aircraft.

Abstract: According to the invention each of the pitch and thrust commands is a linear combination, inter alia, of the trim setting and of the speed setting, and the control provided by the aircraft joystick is pitch rate control. Protection may be provided with respect to trim, angle of incidence, and vertical load factor.