| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 飞机起落架 | CN201380010424.X | 2013-03-21 | CN104136318A | 2014-11-05 | 斯图尔特·莱西; 杰夫·卡姆勒; 皮特·迈克利兹 |
| 一种飞机起落架(10)，包括噪声产生部(12)和遮盖件(14)。所述遮盖件(14)包括遮盖部(14a)，以用于对所述噪声产生部进行包裹，以在所述飞机起落架在使用中时，抑制气流对所述噪声产生部的冲击。 | ||||||
| 2 | 用于飞机起落架的快速释放组件 | CN201180058732.0 | 2011-10-14 | CN103596843B | 2017-04-26 | C.T.奥康奈尔 |
| 一种用于飞机起落架的转矩联杆构件，包括：用于连接至飞机起落架的下部或上部的第一端以及用于连接至另一转矩联杆构件的第二端。锁销安置在上部、下部、第一端或第二端中的一个上。锁销可在接合位置与脱离位置之间轴向地移动，在接合位置，锁销突出，以与第一端、第二端、上部、下部或其它转矩联杆构件的第二端上的配合孔接合。锁销朝接合位置偏压并且可抵抗所述偏压移动至脱离位置。 | ||||||
| 3 | 飞机起落架以及降低飞机起落架噪声的方法 | CN201380010424.X | 2013-03-21 | CN104136318B | 2016-09-21 | 斯图尔特·莱西; 杰夫·卡姆勒; 皮特·迈克利兹 |
| 一种飞机起落架(10)，包括噪声产生部(12)和遮盖件(14)。所述遮盖件(14)包括遮盖部(14a)，以用于对所述噪声产生部进行包裹，以在所述飞机起落架在使用中时，抑制气流对所述噪声产生部的冲击。 | ||||||
| 4 | 用于飞机起落架的快速释放组件 | CN201180058732.0 | 2011-10-14 | CN103596843A | 2014-02-19 | C.T.奥康奈尔 |
| 一种用于飞机起落架的转矩联杆构件，包括：用于连接至飞机起落架的下部或上部的第一端以及用于连接至另一转矩联杆构件的第二端。锁销安置在上部、下部、第一端或第二端中的一个上。锁销可在接合位置与脱离位置之间轴向地移动，在接合位置，锁销突出，以与第一端、第二端、上部、下部或其它转矩联杆构件的第二端上的配合孔接合。锁销朝接合位置偏压并且可抵抗所述偏压移动至脱离位置。 | ||||||
| 5 | Fast withdrawal assembly, and, aircraft landing gear | JP2013534979 | 2011-10-14 | JP2014504224A | 2014-02-20 | チャールズ、ティー．、オコネル |
| 航空機着陸装置のためのトルクリンク部材は、航空機着陸装置の下側部分または上側部分に接続する第１端部と、他のトルクリンク部材に接続する第２端部とを備える。 ロックピンは、上側部分、下側部分、第１端部、第２端部の１つに接して取り付けられている。 ロックピンは、それらの係合位置（ピンが、第１端部、第２端部、上側部分と、下側部分と、他のトルクリンク部材の第２端部と、のいずれかの協調動作用の隙間と相互接続するために突き出る位置）と離脱位置の間で、軸方向に移動可能である。 ロックピンは、係合位置の方へ付勢され、離脱位置への加力に抗して移動可能である。 | ||||||
| 6 | 高速離脱アセンブリ、および、航空機着陸装置 | JP2013534979 | 2011-10-14 | JP6158706B2 | 2017-07-05 | チャールズ、ティー.、オコネル |
| 7 | AERODYNAMIC NOISE REDUCING THIN-SKIN LANDING GEAR STRUCTURES AND MANUFACTURING TECHNIQUES | US15188651 | 2016-06-21 | US20170361923A1 | 2017-12-21 | Richard A. Himmelmann; Stephen E. Tongue |
| A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added. | ||||||
| 8 | Capacitive sensors for monitoring loads | US13272317 | 2011-10-13 | US08933713B2 | 2015-01-13 | Odd Harald Steen Eriksen; Christopher Sanden |
| A sensor for monitoring loads in a landing gear torque linkage includes a main pin having an axial interior bore defined therein. The main pin is configured and adapted to engage a torque link to a strut lug of a landing gear strut. A core pin is mounted axially within an interior bore of the main pin and is spaced radially inwardly from the interior bore for relative displacement with respect to the main pin. A capacitor is included having an inner capacitor plate mounted to the core pin. An outer capacitor plate is mounted to the main pin. Relative displacement of the core pin and the main pin due to loads acting on the torque link and strut lug results in relative displacement of the inner and outer capacitor plates. Signals can thereby be produced indicative of the loads acting on the torque link. | ||||||
| 9 | Towing adapter | US13790938 | 2013-03-08 | US08690180B1 | 2014-04-08 | Ronald R. Baade; John E. Callahan; Gary C. Good |
| A towing adapter can be used during towing of an airplane. The adapter is made of rigid steel with a rubber under-coating and includes two Velcro straps. The device is strapped to two folding struts that are folded down from the wheel assembly of the aircraft. It has a specific angle that keeps the struts at a certain angle with respect to each other, so that struts are accessible to users and is prevented from falling down and injuring someone or causing damage. The device can be easily removed when the towing is finished, and the struts are folded back up onto the plane. | ||||||
| 10 | Torque arm quick disconnect assembly | US73633447 | 1947-03-21 | US2487329A | 1949-11-08 | GERRY JULIAN E |
| 11 | AIRCRAFT LANDING GEAR ASSEMBLY | US15950701 | 2018-04-11 | US20180304999A1 | 2018-10-25 | Robert Kyle Schmidt; Neil Price |
| An aircraft landing gear assembly having a main strut pivotally coupled to an aircraft, a bogie beam pivotally connected to the main strut, a first axle mounted at the first end of the bogie beam and arranged to carry one or more first wheel assemblies and brake assemblies, each first brake assembly being attached to the bogie beam by a brake rod, and a second axle mounted at a second end of the bogie beam and arranged to carry one or more second wheel assemblies and brake assemblies. A double acting actuator is coupled between the strut and the bogie beam to apply a compressive or tensile force to the bogie beam. The ends of the bogie beam are arranged to position the bogie pivot axis below a plane intersecting the axes of rotation of the first and second wheel assemblies when the strut is in the deployed condition. | ||||||
| 12 | Quick release assembly for aircraft landing gear | US13384480 | 2011-10-14 | US09120566B2 | 2015-09-01 | Charles T. O'Connell |
| A torque link member for aircraft landing gear includes a first end for connecting to a lower portion or an upper portion of the aircraft landing gear and a second end for connecting to another torque link member. A locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position wherein the pin protrudes for interengagement with a cooperating aperture on the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member, and a disengaged position. The locking pin is biased toward the engaged position and movable against the biasing to the disengaged position. | ||||||
| 13 | CAPACITIVE SENSORS FOR MONITORING LOADS | US13272317 | 2011-10-13 | US20120043417A1 | 2012-02-23 | Odd Harald Steen Eriksen; Christopher Sanden |
| A sensor for monitoring loads in a landing gear torque linkage includes a main pin having an axial interior bore defined therein. The main pin is configured and adapted to engage a torque link to a strut lug of a landing gear strut. A core pin is mounted axially within an interior bore of the main pin and is spaced radially inwardly from the interior bore for relative displacement with respect to the main pin. A capacitor is included having an inner capacitor plate mounted to the core pin. An outer capacitor plate is mounted to the main pin. Relative displacement of the core pin and the main pin due to loads acting on the torque link and strut lug results in relative displacement of the inner and outer capacitor plates. Signals can thereby be produced indicative of the loads acting on the torque link. | ||||||
| 14 | AIRCRAFT LANDING GEAR | EP13713950.7 | 2013-03-21 | EP2830937B1 | 2018-07-04 | LACY, Stuart; CUMNER, Geoff; MICHAELIDES, Peter |
| An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use. | ||||||
| 15 | QUICK RELEASE ASSEMBLY FOR AIRCRAFT LANDING GEAR | EP11834911.7 | 2011-10-14 | EP2630036B1 | 2018-03-28 | O'CONNELL, Charles, T. |
| A torque link member for aircraft landing gear includes a first end for connecting to a lower portion or an upper portion of the aircraft landing gear and a second end for connecting to another torque link member. A locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position wherein the pin protrudes for interengagement with a cooperating aperture on the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member, and a disengaged position. The locking pin is biased toward the engaged position and movable against the biasing to the disengaged position. | ||||||
| 16 | Nose landing gear arrangement for aircraft and method of assembly | US13674303 | 2012-11-12 | US09302767B2 | 2016-04-05 | Brian G. Cook; John Louis; Thomas Van de Ven; Robert M. Vieito |
| A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft. | ||||||
| 17 | AIRCRAFT LANDING GEAR | US14388489 | 2013-03-21 | US20150053816A1 | 2015-02-26 | Stuart Lacy; Geoff Cumner; Peter Michaelides |
| An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use. | ||||||
| 18 | NOSE LANDING GEAR ARRANGEMENT FOR AIRCRAFT AND METHOD OF ASSEMBLY | US13674303 | 2012-11-12 | US20140131514A1 | 2014-05-15 | Brian G. Cook; John Louis; Thomas Van de Ven; Robert M. Vieito |
| A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft. | ||||||
| 19 | QUICK RELEASE ASSEMBLY FOR AIRCRAFT LANDING GEAR | US13384480 | 2011-10-14 | US20120132742A1 | 2012-05-31 | Charles T. O'Connell |
| A torque link member for aircraft landing gear includes a first end for connecting to a lower portion or an upper portion of the aircraft landing gear and a second end for connecting to another torque link member. A locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position wherein the pin protrudes for interengagement with a cooperating aperture on the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member, and a disengaged position. The locking pin is biased toward the engaged position and movable against the biasing to the disengaged position. | ||||||
| 20 | Device for preventing sliding parts from rotating | US78513047 | 1947-11-10 | US2551410A | 1951-05-01 | MARIE AUDEMAR PIERRE GUILLAUME |
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