IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0394535
(2010-09-06)
|
등록번호 |
US-8616493
(2013-12-31)
|
우선권정보 |
IT-BS2009A0165 (2009-09-10) |
국제출원번호 |
PCT/IT2010/000385
(2010-09-06)
|
§371/§102 date |
20120306
(20120306)
|
국제공개번호 |
WO2011/030365
(2011-03-07)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
12 |
초록
▼
The invention concerns a device and a method to cause the rotation of at least one wheel of the landing gear of aircraft, according to which between the supporting structure (12) of the landing gear and the brake group of the wheel is placed at least an actuator element with variable geometry (35) c
The invention concerns a device and a method to cause the rotation of at least one wheel of the landing gear of aircraft, according to which between the supporting structure (12) of the landing gear and the brake group of the wheel is placed at least an actuator element with variable geometry (35) controlled and managed to develop such a force in order to impose an intermittent angular rotation of the wheel (15) when the brake group is operated.
대표청구항
▼
1. Device for the rotation of at least one wheel of a landing gear, for movement of an aircraft on the ground, the landing gear comprises a shaft carried by a stationary supporting structure, a wheel rim rotating on or with said shaft, a brake set with a turning part associated and turning with the
1. Device for the rotation of at least one wheel of a landing gear, for movement of an aircraft on the ground, the landing gear comprises a shaft carried by a stationary supporting structure, a wheel rim rotating on or with said shaft, a brake set with a turning part associated and turning with the wheel rim and a statoric part associated with said shaft by a sleeve integral with a flange, and a mechanism to apply and release the brake set, the sleeve and flange (21, 22) are capable of angular movements on said shaft, wherein between the supporting structure (12) of the landing gear and the brake set (19, 20) is mounted at least one actuator element with variable geometry (35, 39, 40, 42) controlled and managed to provide sufficient force to cause the flange (22) move through an angular movement on said shaft and cause an intermittent rotation of the wheel when the brake set is applied and, by this, said flange becomes integral with the wheel rim. 2. Device according to claim 1, wherein the at least one actuator element with variable geometry (35) is constrained on one side, directly or indirectly, to said supporting structure (12) and on an opposite side is connected at a tangent to said flange (22). 3. Device according to claim 1, wherein the at least one actuator element with variable geometry (39) is mounted between said flange (22) and an added disk (38) rigidly constrained to said supporting structure, the actuator element being oriented at a tangent between, and connected to, said flange on one side and to said fixed disk on an opposite side. 4. Device according to any of claim 1, wherein the at least one actuator element with variable geometry is variable in length and is provided with a hydraulic cylinder. 5. Device according to claim 1, wherein at least an actuator element with variable geometry comprises a linear electric or an electromechanical actuator. 6. A method for causing the rotation of at least one wheel of a landing gear of an aircraft through a brake set associated with the wheel, where the brake set has a part of it constrained to a flange capable of angular movements on and relatively to a shaft acting as a rotation axis of the wheel, comprising the steps of: a. connecting at least one control actuator element to said flange to be switched on and switched off, under control, on the basis of an active and idle state of the brake set,b. operating, starting from an initial idle position, said control actuator element for applying a tangential force to said flange so as to cause its angular movement when the brake set is active and to transmit a corresponding angular rotation of the wheel through said brake set,c. deactivating the brake set and said at least one actuator element on termination of said angular movement of the flange to return the flange and the actuator to their initial positions,d. repeating in sequence steps b. and c. for an intermittent unidirectional rotation of the wheel. 7. Method according to claim 6, wherein the control actuator of said flange is managed to be switched on and switched off according to the rotation speed of the wheel, said rotating speed being directly or indirectly measurable. 8. Method according to claim 6, wherein when the aircraft is initially on the ground and the wheel is idle, in sequence the operation of the brake set is enabled, the control actuator is operated to cause by its stroke and by the brake set of the wheel an angular movement of the flange, and, at the proximity of the end of the stroke of said actuator, the brake set and the actuator element are deactivated, leaving the wheel to continue to turn, supporting the inertia of the aircraft, while the at least one actuator element returns to an initial position. 9. Method according to claim 6 wherein, with the aircraft on the ground and the wheel rotating in sequence, the actuator element is operated when the brake set is idle, the brake set is activated when the rotation speed of the wheel and the speed which the actuator would set for the wheel on applying the operation of the brake set, are basically the same, so as to cause the rotation of the wheel through the actuator element, and that, at the proximity of the end of the stroke of said actuator, the brake set is deactivated and the at least one actuator element is switched off for its return to an initial position. 10. Method according to claim 6, wherein when the landing gear has several wheels each made to turn by at least a control actuator, the operation of said wheels can be operated in a timely graduated way.
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