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公开(公告)号：EP2277774A1
公开(公告)日：2011-01-26
申请号：EP10011136.8
申请日：2005-06-20
申请人： Goodrich Corporation
发明人： Levoir, Barry , Lavigne, Paul, J.
CPC分类号： B64C25/34 , B64C25/12 , B64C2025/345
摘要： A landing gear for aircraft is characterized by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.
摘要翻译： 用于飞行器的起落架的特征在于俯仰调整致动器（30），其在起落和延伸期间将起落架卡车（16）成比例地与冲击支柱（14）的缩回角度成比例地定位。
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公开(公告)号：EP1424279A4
公开(公告)日：2010-10-20
申请号：EP02758884
申请日：2002-09-05
申请人： YOSHIOKA KOJI , ARUZE CORP
发明人： YOSHIOKA KOJI
CPC分类号： B64C25/60 , B64C25/001 , B64C25/10 , B64C2025/008
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公开(公告)号：EP2195237A2
公开(公告)日：2010-06-16
申请号：EP08836934.3
申请日：2008-10-13
发明人： BENNETT, Ian
CPC分类号： B64C25/34 , B64C25/58 , B64D2045/008 , F16F9/3264
摘要： A landing gear for an aircraft comprises: a shock absorber strut (1) with upper and lower telescoping portions (2, 3), the upper portion (2) being connectable to the airframe of the aircraft; an arm (4) to extend fore and aft relative to the aircraft and carrying a landing wheel, (7, 7
1 ), and pivotally connected by a main pivot (5) to the lower portion (3) of the shock absorber strut; and a load reacting unit (9) connected between the arm (4) and the shock absorber strut (1) for reacting to load applied between the arm and shock absorber strut on landing, and an indicator (60) for monitoring the load applied to the load reacting unit (9) on landing. The load reacting unit (9) may be connected between a forward end of the arm (4) and the upper portion (2) of the shock absorber strut to make the gear act as a semi-levered landing gear. Alternatively, the load reacting unit (9) may be connected between the arm (4) and the lower portion (3) of the shock absorber strut to act as a pitch trimmer. The arm (4) may comprise a bogie beam with fore and aft landing wheels (7, 7
1 ) with the main pivot (5) therebetween. The load reacting unit (9) preferably comprises a fluid pressure unit and the indicator (60) comprises a mechanical indicator that operates at a predetermined pressure threshold.-
公开(公告)号：EP2085309A3
公开(公告)日：2009-12-02
申请号：EP09160692.1
申请日：2006-08-04
摘要： A semi-levered landing gear for an aircraft comprising: a main shock absorber strut (1) with upper and lower telescoping portions, with the upper portion (2) connectable to the airframe; a bogie beam (4) to extend fore and aft of the aircraft fuselage with at least one forward axle and one aft axle for respective forward and aft wheels and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut; and an auxiliary mechanism comprising a lever unit (92), a spring unit (94) and a positioning unit (90), with a first one of said units pivotally connected to the upper portion of the main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position, a second one of said units pivotally connected at an upper end to the upper portion of the main shock absorber strut and pivotally connected at a lower end to the first one of said units, and a third one of said units pivotally connected at a lower end to the bogie beam at an auxiliary pivot and connected at an upper end to the lever, the positioning unit assuming one of a contracted state or extended state for taxiing, take-off and landing, and the other of the contracted or extended state for stowing the landing gear after take-off, and the spring unit providing spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing.
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公开(公告)号：EP1773656A2
公开(公告)日：2007-04-18
申请号：EP05856830.4
申请日：2005-06-20
申请人： Goodrich Corporation
CPC分类号： B64C25/34 , B64C25/12 , B64C2025/345
摘要： A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.
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公开(公告)号：EP1171343B1
公开(公告)日：2007-01-17
申请号：EP00917902.9
申请日：2000-03-13
申请人： The Boeing Company
发明人： LINDAHL, Gary, M.
CPC分类号： B64C25/58 , B64C25/22 , F15B11/028 , F15B15/1409 , F15B15/149 , F15B2211/30505 , F15B2211/40507 , F15B2211/41536 , F15B2211/50518 , F15B2211/50527 , F15B2211/5153 , F15B2211/55 , F15B2211/57 , F15B2211/7057 , F15B2211/76 , F15B2211/8613 , F15B2211/865 , F16F9/18
摘要： A combine hydraulic damper and truck positioner mechanism (20) for a landing gear (22) of an airplane. The landing gear being swingingly attached to the airplane for reciprocating movement of the landing gear between an extended position and a retracted position. The landing gear including an elongate main strut (24) having one end swingingly attached to the airplane and a longitudinally spaced second end (36). The landing gear futher including a truck beam assembly (26) pivotally attached to the strut second end. The truck beam assembly having at least two wheels (30) journaled thereto. The combined damper and truck positioner mechanism including a housing (60) having one end (68) adapted to be fastened to the strut. The housing having an interior bore (66) with a predetermined cross-sectional area. The combined damper and truck positioner mechanism further including a piston (64) having a first piston head end (90) and a longitudinally spaced second end (112) adapted to be fastened to the truck beam assembly. The piston head being slidably received within the bore for sliding movement of the piston in response to pivoting movement of the truck beam assembly when the piston second end is attached to the truck beam assembly. The combined damper and truck positioner mechanism also including a damping assembly (54) in fluid communication with the housing. The damping assembly maintaining a substantially constant fluid pressure withint the housing to dampen loads associated with the sliding movement of the piston when the landing gear is in the extended position.
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157.发明授权
公开(公告)号：EP1581424B1
公开(公告)日：2006-08-16
申请号：EP03815705.3
申请日：2003-12-29
申请人： MESSIER-DOWTY S.A.
IPC分类号： B64C25/58
CPC分类号： B64C25/58 , B64C25/60 , B64C2025/008 , B64C2025/125
摘要： The invention concerns an aircraft landing gear strut damper of the type comprising a main strut assembly (11) and a piston rod (13) delimiting with the strut assembly (11) a main chamber (14) and an annular chamber (15) of hydraulic fluid, and having internally two adjacent chambers (19, 20) isolated from each other by a separating piston (21). The invention is characterized in that the damper (10) further comprises a first auxiliary strut assembly (26) sliding telescopically on said piston-rod (13), as well as a second auxiliary strut assembly (37) sliding telescopically on the other end of the first auxiliary strut assembly (26). The two auxiliary annular chambers (31, 40) thus delimited are connected each to an associated control circuit thereby enabling the total length of the damper to be shortened or lengthened for respectively collapsing or extending the landing gear strut.
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158.发明公开
公开(公告)号：EP1633993A1
公开(公告)日：2006-03-15
申请号：EP04739438.2
申请日：2004-05-28
摘要： The present invention refers to an apparatus for absorbing energy attenuating a force caused by an impact. In particular it refers to a triggering system for the plastic collapse of a metal structural element, particularly suitable for attenuating forces generated by high-velocity impacts, such as in the case of aircraft accidents. In one embodiment the triggering system for the plastic collapse of a metal structural element comprises: an elongated tubular element (11); a fixed ring (1) having a plurality of wedge-shaped flanges (3) associated to said elongated tubular element; a mobile element (2) sliding in the direction of said elongated tubular element and associated with said fixed ring; said mobile element, in response to its movement in the direction of said wedge-shaped flanges, interacts with said wedge-shaped flanges which in turn interact with said elongated tubular element so as to trigger a collapse of said elongated tubular element.
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公开(公告)号：EP1424279A1
公开(公告)日：2004-06-02
申请号：EP02758884.7
申请日：2002-09-05
申请人： Yoshioka, Koji , Aruze Corp.
发明人： YOSHIOKA, Koji
IPC分类号： B64C25/58
CPC分类号： B64C25/60 , B64C25/001 , B64C25/10 , B64C2025/008
摘要： An aircraft wheel support mechanism capable of reducing the impact to the tire at the time of landing and capable of reducing the impact to the tire at the time of the wheel colliding with an obstacle lying on the runway. The mechanism comprises a suspension mechanism (3) for rotatably supporting a wheel (13) by the lower end of a support member (2) connected to the fuselage, the suspension mechanism (3) having a crank shaft assembly (5), and is characterized in that the crank shaft assembly comprises a horizontal support shaft (51) rotatably supported by the lower end of the support member, an axle (52) for rotatably supporting the wheel, and an arm (53) positioned at right angles with the horizontal support shaft and axle for connecting one end of the horizontal support shaft to one end of the axle.
摘要翻译： 一种飞机轮支撑机构，其能够降低着陆时对轮胎的冲击，并且能够减少在轮子与跑道上的障碍物碰撞时对轮胎的冲击。 该机构包括用于通过连接到机身的支撑构件（2）的下端可旋转地支撑车轮（13）的悬架机构（3），悬架机构（3）具有曲轴组件（5），并且 其特征在于，所述曲轴组件包括由所述支撑构件的下端可旋转地支撑的水平支撑轴（51），用于可旋转地支撑所述轮子的轴（52）和与所述水平轴成直角布置的臂（53） 支撑轴和轴，用于将水平支撑轴的一端连接到轴的一端。
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公开(公告)号：EP0551042A1
公开(公告)日：1993-07-14
申请号：EP92403567.8
申请日：1992-12-29
申请人： MESSIER BUGATTI
发明人： Derrien, Michel , Guyot, Bernard
CPC分类号： B64C25/60 , B60G2202/152 , B60G2202/24 , B60G2800/20 , B64C25/001 , B64C2025/008 , F16F9/06 , F16F9/18
摘要： L'invention concerne un amortisseur du type comportant un caisson et une tige coulissante, avec un fond mobile délimitant une chambre inférieure de fluide hydraulique qui communique, par l'intermédiaire d'un diaphragme, avec une chambre supérieure de fluide hydraulique adjacente à une chambre à gaz sous pression ménagée en partie haute du caisson.
Conformément à l'invention, un actionneur linéaire indépendant (130.1) est disposé dans la tige coulissante (102), coaxialement à celle-ci, en étant interposé entre le fond mobile (112) et une butée inférieure (126) solidaire de ladite tige coulissante, des moyens autonomes (150.1) étant en outre prévus pour la commande de l'actionneur linéaire, moyens dont l'enclenchement permet d'obtenir un rehaussement du train d'atterrissage lorsque l'aéronef est à l'arrêt au sol.
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