Method and apparatus for control of a steerable landing gear
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/50
G05D-001/02
B64C-019/00
출원번호
US-0016677
(2016-02-05)
등록번호
US-9802696
(2017-10-31)
우선권정보
GB-1501939.1 (2015-02-05)
발명자
/ 주소
Garaygay, Cecile
Romana, Louis-Emmanuel
Mayolle, Matthieu
출원인 / 주소
Airbus Operations Limited
대리인 / 주소
Nixon & Vanderhye P.C.
인용정보
피인용 횟수 :
1인용 특허 :
5
초록▼
A slip-reduction control unit for an aircraft having a steerable landing gear. The control unit receives steering input signals from which a target steering command output may be ascertained and additional input signals (a) the motion of the aircraft, (b) a steering angle, or (c) a parameter relatin
A slip-reduction control unit for an aircraft having a steerable landing gear. The control unit receives steering input signals from which a target steering command output may be ascertained and additional input signals (a) the motion of the aircraft, (b) a steering angle, or (c) a parameter relating to the slip sustained by the steerable landing gear. The slip-reduction control unit determines, based on the additional input signals, reduces the rate of change of steering angle that would otherwise be commanded. The reduction in the rate of change may reduce vibration on the aircraft that might be caused by a greater rate of change in the steering angle.
대표청구항▼
1. A slip-reduction control unit configured to be employed on an aircraft having a longitudinal axis and a steerable landing gear including one or more steerable wheels, wherein the slip-reduction control unit is configured to (i) receive a steering input signal from which a target steering command
1. A slip-reduction control unit configured to be employed on an aircraft having a longitudinal axis and a steerable landing gear including one or more steerable wheels, wherein the slip-reduction control unit is configured to (i) receive a steering input signal from which a target steering command output is ascertained, and (ii) receive one or more additional input signals concerning at least one of (a) the motion of the aircraft, (b) a steering angle, and (c) a parameter relating to the slip sustained by the steerable landing gear, and the slip-reduction control unit is configured so that, in dependence on the one or more additional input signals, a rate of change of an angle of the one or more steerable wheels that would otherwise be commanded is reduced. 2. The slip-reduction control unit according to claim 1, wherein the slip-reduction control unit is configured to output a steering command which is selected such that the rate of change of the angle of the one or more steerable wheels is less than a steering rate threshold value. 3. The slip-reduction control unit according to claim 2, wherein the steering rate threshold value is calculated in dependence on the additional input signals. 4. The slip-reduction control unit according to claim 2, wherein the steering rate threshold value is subject to an absolute maximum steering rate threshold value. 5. The slip-reduction control unit according to claim 1, wherein the one or more additional input signals comprise an aircraft speed signal and a steering angle signal representing a steering angle. 6. The slip-reduction control unit according to claim 1, wherein a steering command outputted by the slip-reduction control unit effects active turning of the one or more steerable wheels by means of actuators acting on the steerable landing gear. 7. The slip-reduction control unit according to claim 1, wherein the steering input signal received by the slip-reduction control unit comprises one or more signals from a pilot-operable steering tiller device. 8. An aircraft including the slip-reduction control unit recited in claim 1. 9. The aircraft according to claim 8, including one or more actuators for steering a steerable landing gear anda further steering control system configured to modify steering command signals that are sent to the one or more actuators,wherein the slip-reduction control unit performs a distinct and separate function from the further steering control system. 10. The slip-reduction control unit of claim 1 wherein the slip-reduction control unit is provided separately from the aircraft. 11. A computer program product configured to cause, when the computer program is executed, a computer implemented aircraft slip-reduction control unit to perform the function of the slip-reduction control unit of claim 1. 12. A method of reducing vibration on an aircraft caused by steering effected by a steerable nose landing gear comprising controlling a rate of change of the angle of the steerable nose landing gear, wherein the controlling the rate of change of the angle of the steerable nose landing gear is performed in dependence on values concerning at least one of (a) the motion of the aircraft, (b) a steering angle, and (c) a parameter relating to the slip sustained by the steerable landing gear. 13. The method according to claim 12, wherein the controlling the rate of change of the angle of the steerable nose landing gear is effected by directly controlling the rate of change of the angle of the steerable nose landing gear. 14. The method according to claim 12, wherein the controlling the rate of change of the angle of the steerable nose landing gear is effected by setting a threshold for a maximum permitted rate of change of the angle of the steerable nose landing gear. 15. The method of claim 12 wherein the controlling of the rate of change of the angle of the steerable nose landing gear is performed by a slip-reduction control unit. 16. A computer program stored on a non-transitory storage media and configured to be executed by a processor in a slip-reduction control unit on an aircraft having a longitudinal axis and a steerable landing gear wheel, wherein the execution of the computer program causes the slip-reduction control unit to: receive a steering input signal;generate a target steering command output based on the received steering input signal;based on the target steering command output, determine a rate of change of a steering angle to turn the steerable landing gear wheel;receive an additional input signal indicating at least one of (a) a motion of the aircraft, (b) a steering angle for the steerable landing gear wheel, and (c) a parameter relating to slip sustained by the steerable landing gear wheel; andbased on the additional input signal, reduce the rate of change of the steering angle. 17. A method to control a steering angle of a steerable landing gear for an aircraft comprising: receive a steering input signal;generate a target steering command output based on the received steering input signal;based on the target steering command output, determine a rate of change of a steering angle to turn the steerable landing gear wheel;receive an additional input signal indicating at least one of (a) a motion of the aircraft, (b) a current steering angle of the steerable landing gear wheel, and (c) a parameter relating to a current slip sustained by the steerable landing gear wheel with respect to a runway;determine a maximum rate of change of the steering angle based on the additional input signal;reduce the determined rate of change to at most the maximum rate of change, andturn the steerable landing gear wheel at the reduced determined rate of change of the steering angle.
Chatrenet, Dominique; Villaumé, Fabrice; Bourissou, Céline; Scacchi, Pierre; Romana, Louis-Emmanuel, Method and device for the lateral control of a taxiing aircraft.
Tada, Kazunari; Furuichi, Kazushi; Minami, Yutaro, Method of controlling steering control equipment for aircraft, and steering control equipment for aircraft and aircraft provided therewith.
Guignard, Fabien; Venilal, Priteche, Method and device for estimating a lateral speed and a lateral position of an aircraft, during a phase where the aircraft is traveling on the ground.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.