Shock absorber for use in lowering aircraft landing gear
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-025/58
F16F-009/46
F16F-009/18
출원번호
US-0019848
(1993-02-19)
우선권정보
FR-0002016 (1992-02-21)
발명자
/ 주소
Derrien Michel (Versailles FRX)
출원인 / 주소
Messier-Bugatti (Velizy Villacoublay FRX 03)
인용정보
피인용 횟수 :
18인용 특허 :
0
초록▼
The invention relates to a shock absorber comprising a main body and a rod-piston, with the rod-piston being retracted when the landing gear is down and extended when the landing gear is up. The main body comprises, in succession, three chambers that are separated by associated partitions, and that
The invention relates to a shock absorber comprising a main body and a rod-piston, with the rod-piston being retracted when the landing gear is down and extended when the landing gear is up. The main body comprises, in succession, three chambers that are separated by associated partitions, and that comprise: a first hydraulic chamber in which the rod-piston slides freely; a chamber in which a separator piston slides, delimiting a second hydraulic chamber; and a chamber in which another piston slides, delimiting both a third hydraulic chamber and a chamber containing gas under high pressure. Communication means are provided between said chambers together with two associated electrically controlled valves enabling corresponding fluid connections to be selectively established. Thus, in a normal regime, the shock absorber enables a certain amount of energy to be stored while the landing gear is being lowered, which energy is restored next time the landing gear is raised; while during an emergency regime, the shock absorber participates in braking the landing gear while it is being lowered in an emergency, e.g. under its own weight after a jammed lowering actuator has been declutched.
대표청구항▼
A shock absorber for use in lowering aircraft landing gear, the shock absorber comprising a main body and a rod-piston, said shock absorber being disposed between a point on the landing gear and a fixed point of the airplane structure in such a manner that the rod-piston is retracted when the landin
A shock absorber for use in lowering aircraft landing gear, the shock absorber comprising a main body and a rod-piston, said shock absorber being disposed between a point on the landing gear and a fixed point of the airplane structure in such a manner that the rod-piston is retracted when the landing gear is down and extended when the landing gear is in up, wherein the main body comprises, in succession, three chambers separated by associated intermediate partitions of said body, providing a first hydraulic fluid chamber in which the rod-piston slides freely, a chamber adjacent to said first chamber in which a first separator piston slides, delimiting a second hydraulic fluid chamber and a chamber that is connected to the atmosphere, and a last chamber in which a second separator piston slides, delimiting a third hydraulic fluid chamber and a chamber of gas under high pressure, said first separator piston having an axial rod which penetrates into said gas chamber by passing through said second separator piston, and wherein said shock absorber further includes communication means between the first hydraulic fluid chamber and each of the second and third hydraulic fluid chambers, with two associated electrically controlled valves enabling a fluid connection to be selectively established with one or other of said second and third chambers so as to obtain two operating regimes for the shock absorber, including a normal regime in which the second separator piston acts on its own and enables a certain amount of energy to be stored on lowering of the landing gear, which energy can be reused during subsequent raising of said landing gear, and an emergency regime in which the first separator piston acts on its own and participates in braking the emergency lowering of the landing gear.
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