초록 ▼

The invention relates to novel basic architecture for helicopter autopilots, transforming the conventional objective of maintaining fuselage trim to an objective of maintaining airspeed, and without making use of coupler techniques. On each of the pitch and roll control systems, a known fraction of

The invention relates to novel basic architecture for helicopter autopilots, transforming the conventional objective of maintaining fuselage trim to an objective of maintaining airspeed, and without making use of coupler techniques. On each of the pitch and roll control systems, a known fraction of the output signal (24S) from the flight control is injected by being summed with the standard fuselage trim input (1S). The signal (4S) formed in this way possesses the novel static and dynamic properties required for the control loop to make the helicopter statically stable in speed throughout its flight envelope. The novel architecture makes it possible to replace the conventional fuselage trim signal (1S) with an accelerometer signal. The signal (4S) is displayed in particular on a standard "artificial horizon" type instrument (33), thereby making it possible simultaneously to monitor rapid variations of fuselage trim and to control airspeeds.

대표청구항 ▼

[ I claim:] [1.] Apparatus for assisting automatic piloting of rotating wing aircraft for the purpose of keeping the lateral and longitudinal components of the airspeed equal to desired reference values therefore, the apparatus comprising two systems, one for roll and the other for pitch, each of sa

[ I claim:] [1.] Apparatus for assisting automatic piloting of rotating wing aircraft for the purpose of keeping the lateral and longitudinal components of the airspeed equal to desired reference values therefore, the apparatus comprising two systems, one for roll and the other for pitch, each of said systems having means (1) for generating a signal (1S) that is a function of the trim of the fuselage, summing means having one input receiving said signal that is a function of the trim of the fuselage, integrator means (5) for generating a reference signal (5S), said reference signal being applied as an input of the summing means, means for actuating cyclic flight controls as a function of an output signal of the summing means, cyclic position means (24) for generating a signal (24S) that is a function of the position of the cyclic control for the blades of at least one main rotor the apparatus being characterized in that the output of said cyclic position means (24) is connected to the input of the summing means (4, 3, 10), the summing means (4, 3, 10) producing a weighted sum of the signal (15) of the trim of the fuselage and of the signal (24S) that is a function of the position of the cyclic control, the integrator means (5) being such that the output signal of said integrator means (5) is representative of a reference airspeed.