초록 ▼

Method and device for reducing the vibratory motions of the fuselage of an aircraft.According to the invention, accelerometers ( 9, 10 ) are mounted on engines (M 1 , M 4 ) of the aircraft ( 1 ) and, with the aid of the accelerometric measurements thus obtained and of the aeroelastic model of said a

Method and device for reducing the vibratory motions of the fuselage of an aircraft.According to the invention, accelerometers ( 9, 10 ) are mounted on engines (M 1 , M 4 ) of the aircraft ( 1 ) and, with the aid of the accelerometric measurements thus obtained and of the aeroelastic model of said aircraft, control commands (dZ, dY) to be applied to the ailerons (M 1 to M 4 ) so as to counteract the oscillations of said engines are determined.

대표청구항 ▼

1. A method for reducing vibratory motions of a fuselage of an aircraft, said vibratory motions being engendered by engines of said aircraft which comprises two fixed wings which are symmetric with respect to said fuselage, each of said wings being provided with control surfaces articulated to its t

1. A method for reducing vibratory motions of a fuselage of an aircraft, said vibratory motions being engendered by engines of said aircraft which comprises two fixed wings which are symmetric with respect to said fuselage, each of said wings being provided with control surfaces articulated to its trailing edge and bearing at least one of said engines, said method comprising:(a) associating at least one accelerometer with at least one of said engines;(b) measuring accelerations undergone by said at least one of said engines in at least one direction transverse to said at least one of said engines, wherein said direction is horizontal, that is to say lateral with respect to said aircraft;(c) with the aid of the accelerometric measurements thus obtained, determining at least one oscillatory control command which, applied to at least one control surface of the the one of said wings bearing said at least one of said engines, is able to counteract the vibratory motions of said at least one of said engines in said direction; and(d) applying said control command to said at least one control surface. 2. The method as claimed in claim 1, wherein step (C) comprises determining said control command from preestablished relations which emanate from the aeroelastic model, specific to said aircraft, and which, for each acceleration undergone by said aircraft at the location of said at least one of said engines and in said direction, are able to deliver such a said control command. 3. The method as claimed in claim 1, further comprising:(e) associating at least one accelerometer with at least one of said engines of each of said wings;(f) measuring accelerations undergone by each of said engines, thus each equipped with said at least one accelerometer, in at least one direction transverse to said each of said engines;(g) with the aid of accelerometric measurements thus obtained in step (f), determining at least one oscillatory control command which, applied to control surfaces of said wings, is able to counteract the vibratory motions of said engines in said direction of step (f); and(h) applying said control command determined in step (g) to said control surfaces. 4. The method as claimed in claim 2, further comprising:(e) measuring accelerations undergone by two of said engines of said aircraft, which are symmetric with respect to said fuselage, in said direction transverse to said engines;(f) calculating an average of said accelerations undergone by said two symmetric engines;(g) determining a common control command with the aid of said relations preestablished from said aeroelastic model; and(h) applying said common control command to two of said control surfaces which are symmetric with respect to said fuselage. 5. The method as claimed in claim 1, wherein said at least one direction of measurement of said accelerations includes a vertical direction. 6. The method as claimed in claim 1, wherein said at least one control surface is an aileron. 7. The method as claimed in claim 2, in which each wing of said aircraft comprises at least two types of ailerons, namely at least one outer aileron and at least one inner aileron, further comprising:(e) determining a first control command able to counteract vertical vibratory motions of at least two of said engines which are symmetric with respect to said fuselage;(f) determining a second control command able to counteract lateral vibratory motions of said symmetric engines;(f) applying said first control command to at least two ailerons, of one of the two types, disposed symmetrically with respect to said fuselage, in such a way that these two ailerons pull up symmetrically in the same direction; and(f) applying said second control command to at least two ailerons of the other of the two types, likewise disposed symmetrically with respect to said fuselage, in such a way that these two ailerons deflect antisymmetrically in opposite directions. 8. The method as claimed in claim 2, applied to an airc raft comprising several engines per wing, which is implemented only for the outer engines of the aircraft. 9. A device for reducing the vibratory motions of a fuselage of an aircraft, said vibratory motions being engendered by the engines of said aircraft which comprises two fixed wings which are symmetric with respect to said fuselage, each of said wings being provided with control surfaces articulated to its trailing edge and bearing at least one of said engines, said device comprising:(a) accelerometers associated with at least two of said engines mutually symmetric with respect to said fuselage and able to measure the respective accelerations of these engines in at least one direction transverse to said engines, wherein said direction is horizontal, that is to say lateral with respect to said aircraft;(b) at least one table in which are recorded relations preestablished from the aeroelastic model relating specifically to said aircraft;(c) means of calculation able to calculate, with the aid of the accelerometric measurements delivered by said accelerometers and of the preestablished relations of said table, at least one control command which, applied to control surfaces which are symmetric with respect to said fuselage, is able to counteract the vibratory motions of said engines in said direction; and(d) means for applying said control command to said control surfaces. 10. The device as claimed in claim 9, for an aircraft provided with a system of electric flight controls, wherein said means of calculation and said means of application of said control command farm part of said system of electric flight controls.