[특허]Programmed oleo-pneumatic shock absorber

[미국특허] Programmed oleo-pneumatic shock absorber 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F16F-009/18 F16F-009/50
출원번호	US-0214217 (1980-12-08)
발명자 / 주소	Cook, William C.
출원인 / 주소	Lockheed Corporation
대리인 / 주소	Sullivan, John J.
인용정보	피인용 횟수 : 36 인용 특허 : 1

초록 ▼

An improved air/oil shock absorber (16) especially adapted for aircraft landing gears (11) is provided whereby the rate of strut (14) compression is programmed separately for the landing impact and for rollout after the landing. During the landing impact, increased tail clearance is achieved by temporarily delaying the last few inches of compression. After the aircraft rotates on to the nose landing gear, the shock absorber (16) slowly compresses to its static position where it then functions in a conventional manner. The shock absorber assembly (16) may be oriented in any position with respect to the aircraft (10) by virtue of two internal air/oil separator pistons (24 and 29).

대표청구항 ▼

1. A programmed oleo-pneumatic shock absorber for the interconnection of two relatively movable members comprising: an outer cylindrical housing terminating at one end in a closure wall; a first hollow cylindrical piston slidably mounted in the other end of said outer cylindrical housing for telescoping movement internally thereof, said piston terminating at opposite ends in closure walls; attachment means carried by the opposite outer ends of said housing and said first piston, one said attachment means adapted for connection to one of said relatively movable members and the other said attachment means adapted for connection to the other of said relatively movable members; a pair of bearings, one carried internally by said housing adjacent its said other end and one carried externally by said piston adjacent its end internally of said housing to facilitate the movement of said housing and said piston and to define an annular chamber therebetween; at least one passage of predetermined size piercing the bearing carried by said piston end to establish communication between the interior of said housing and said annular chamber; a check valve associated with each said passage to restrict fluid flow between the interior of said housing and said annular chamber; a second hollow cylindrical piston transversely filling, and slidably mounted on and against the inner wall of, said first piston for movement relative to said first piston and said housing, said second piston terminating at opposite ends in closure walls; a slidable bulkhead mounted internally of said second piston; a predetermined quantity of relatively incompressible fluid within said housing, said annular chamber and the ends of said first and second pistons on the side of said slidable bulkhead adjacent said one housing end; a predetermined quantity of relatively compressible fluid within the ends of said first and second pistons on the other side of said slidable bulkhead; and an orifice of predetermined size in the closure wall adjacent the aforesaid telescoping end of said first piston and an orifice of small size relative to said predetermined size in each of said closure walls of said second piston, whereby an initial displacement of said second piston occurs with virtually no displacement of said bulkhead relative to said second piston upon movement of said two relatively movable members and subsequently a measurable displacement of said bulkhead relative to said second piston occurs allowing additional movement of said two relatively movable members. 2. The shock absorber of claim 1 wherein said two relatively movable members are the main support strut and a crank arm carried by the axle of a surface contacting element of an aircraft landing gear unit. 3. The shock absorber of claim 1 wherein said predetermined quantity of relatively compressible and relatively incompressible fluid is such that said first piston is normally fully extended relative to said housing and said second piston and said slidable bulkhead are located adjacent the closure wall of said first piston. 4. The shock absorber of claim 3 wherein the size relationship of said orifices is such that the displacement of said first piston upon initial movement of said relatively movable members is from the fully extended position aforesaid to approximately midway of its telescoped position in said housing prior to said subsequent measurable displacement of said slidable bulkhead. 5. The shock absorber of claim 1 wherein the size relationship of said orifices is such that the fluid flow internally of said shock absorber causes the movement of said relatively movable members at two distinct different speeds throughout the length of travel thereof as determined by said piston and housing telescoping movement from the fully extended to the fully contracted positions, said telescoping movement being at a substantially greater speed during the initial part of said travel than during the latter part of said travel.

이 특허에 인용된 특허 (1) 인용/피인용 타임라인 분석

Masclet ; Jean ; Veaux ; Jacques, Shock absorber.
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이 특허를 인용한 특허 (36) 인용/피인용 타임라인 분석

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Bachmeyer, Paul J.; Hodgson, Doug A., Aircraft front nose landing gear and method of making an aircraft landing gear.
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Bachmeyer, Paul J.; Hodgson, Doug A., Aircraft front nose landing gear and method of making an aircraft landing gear.
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Bachmeyer, Paul Joseph; Hodgson, Doug A., Aircraft front nose landing gear and method of making an aircraft landing gear.
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Bachmeyer, Paul J.; Swanson, Douglas A.; Pittman, Bryan J.; Thompson, Scott K.; Hodgson, Doug A., Aircraft landing gear assembly shimmy damper.
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Bachmeyer, Paul Joseph; Swanson, Douglas A.; Pittman, Bryan J.; Thompson, Scott K.; Hodgson, Doug A., Aircraft landing gear assembly shimmy damper.
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Ditzler, Adam J., Cam-operated bi-directional shock absorber damper.
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Bryant, Malcom S.; Hasenoehrl, Thomas R.; Kilner, Jerome R.; Lindahl, Gary M.; Song, Taiboo, Control system and method for a semi-levered landing gear for an aircraft.
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Lindahl, Gary M.; Nelson, Eric Howard; Mellor, Mitchell Loren Ray, Hydraulic strut assembly for semi-levered landing gear.
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Philippe Joseph (Carpentras FRX) Perrochat Jean-Michel (Montrouge FRX), Hydropneumatic jack.
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Dohrmann, Wolfgang; Krug, Paul Eberhard, Impact damper.
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Cottet, Justin Duane, Landing gear system.
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Kilner Jerome ; Lindahl Gary, Semi-levered landing gear and auxiliary strut therefor.
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Barefoot, Darek C., Shock absorber incorporating a floating piston.
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[미국특허] Programmed oleo-pneumatic shock absorber 원문보기

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이 특허에 인용된 특허 (1) 인용/피인용 타임라인 분석

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[미국특허] Programmed oleo-pneumatic shock absorber 원문보기

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