|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/195; 244/076.C; 701/003; 701/010|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 8 인용 특허 : 13|
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.
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 tran...