公开(公告)号：US10259568B2

公开(公告)日：2019-04-16

申请号：US15378770

申请日：2016-12-14

Applicant: GOODRICH CORPORATION

Inventor： William E. Luce

IPC: B64C25/18 ,  B64C25/26 ,  B64C25/22 ,  G05G5/06 ,  B64C25/20 ,  F16H21/44

Abstract: A non-jamming shrink latch assembly for retractable aircraft landing gear is disclosed. The non-jamming shrink latch assembly may comprise a rod; a hook pivotally coupled to a first rod end of the rod; a lower link having a first lower link end and a second lower link end, wherein the first lower link end is pivotally coupled to the hook; and an upper link pivotally coupled to the second lower link end of the lower link. The hook may be configured to move from a locked position to an open position in response to receiving a mechanical load from the lower link. The hook may also be configured to move from the open position to the locked position in response to receiving a mechanical load from a roller.

公开(公告)号：US20180194460A1

公开(公告)日：2018-07-12

申请号：US15451098

申请日：2017-03-06

Applicant: Goodrich Corporation

Inventor： William E. Luce

IPC: B64C25/60 ,  B64D45/00 ,  F16F9/32 ,  F16F15/023 ,  F16F9/18

CPC classification number: B64C25/60 ,  B64C25/22 ,  B64D45/0005 ,  B64D2045/008 ,  F16F9/18 ,  F16F9/3214 ,  F16F9/3235 ,  F16F9/3292 ,  F16F15/023 ,  G01P5/00

Abstract: A landing detection system for a landing gear assembly of an aircraft may comprise a moveable member mechanically coupled between an aircraft wheel and a strut piston, wherein the moveable member is in communication with a strut chamber pressure of the landing gear assembly, wherein the moveable member moves relative to the strut piston in response to a first force applied to the aircraft wheel and the strut piston strokes in response to a second force applied to the aircraft wheel.

公开(公告)号：US10000279B2

公开(公告)日：2018-06-19

申请号：US15001841

申请日：2016-01-20

Applicant: Goodrich Corporation

Inventor： William E. Luce

IPC: B64C25/10

CPC classification number: B64C25/10

Abstract: The present disclosure describes systems and methods for retractable landing gear. A landing gear arrangement may comprise: a trailing arm; a shock strut; a link rotatably coupled to a first end of the shock strut and rotatably coupled to the trailing arm, the link including a pivot; a rotatable latch rotatably coupled to the link; and an actuator coupled between the rotatable latch and the trailing arm, the rotatable latch configured to rotate about the pivot, the pivot located between a first end and a second end of the rotatable latch, the rotatable latch configured to rotate in a first direction in response to the actuator extending and configured to rotate in a second direction in response to the actuator compressing.

公开(公告)号：US20180058985A1

公开(公告)日：2018-03-01

申请号：US15672075

申请日：2017-08-08

Applicant: Goodrich Corporation

Inventor： William E. Luce ,  Amir Fazeli

IPC: G01M17/04 ,  B64F5/60

CPC classification number: G01M17/04 ,  B64C25/60 ,  B64F5/60

Abstract: A method for monitoring a shock strut may comprise measuring a first shock strut pressure, measuring a first shock strut temperature, measuring a second shock strut pressure, measuring a second shock strut temperature, measuring a shock strut stroke, and determining a servicing condition of the shock strut based upon the first shock strut pressure, the first shock strut temperature, the second shock strut pressure, the second shock strut temperature, and the shock strut stroke and taking into account at least one of an absorption of a gas with a fluid and desorption of the gas with the fluid.In various embodiments, the method may further comprises measuring a third shock strut pressure, measuring a third shock strut temperature, wherein the servicing condition is further based upon the third shock strut pressure and the third shock strut temperature.

公开(公告)号：US08919182B2

公开(公告)日：2014-12-30

申请号：US13963705

申请日：2013-08-09

Applicant: Goodrich Corporation

Inventor： William E. Luce

IPC: G01F25/00 ,  B64C25/60 ,  G01F23/292 ,  G01M3/32 ,  G01M11/00

CPC classification number: G01M11/31 ,  B64C25/60 ,  G01F23/2922 ,  G01F23/2925 ,  G01F25/0061 ,  G01F25/0076 ,  G01M3/3245

Abstract: A system for monitoring a liquid level in an aircraft shock strut includes a cylinder having an internal chamber sealed by a piston telescopically movable within the cylinder. The chamber contains a gas and a liquid, and a sensor assembly is provided for monitoring a condition of a level of the liquid in the chamber. The sensor assembly includes at least one probe within the chamber, and a fitting assembly allows one or more leads from the probe to pass through the wall of the strut while maintaining pressure in the chamber. The fitting assembly includes a plug molded to the one or more leads extending from the probe. The fitting assembly also includes a retainer for holding the plug in sealed relationship with a through passage in the strut.

Abstract translation: 用于监测飞行器冲击支柱中的液位的系统包括具有由可在气缸内可伸缩移动的活塞密封的内部腔室的气缸。 所述腔室包含气体和液体，并且设置有用于监测腔室中液体水平的状态的传感器组件。 传感器组件包括腔室内的至少一个探针，并且接头组件允许来自探针的一个或多个引线穿过支柱的壁，同时保持腔室中的压力。 配件组件包括模制到从探针延伸的一个或多个引线的插头。 装配组件还包括用于将插头与支柱中的通道保持密封关系的保持器。

公开(公告)号：US20130342828A1

公开(公告)日：2013-12-26

申请号：US13963705

申请日：2013-08-09

Applicant: Goodrich Corporation

Inventor： William E. Luce

IPC: G01M11/00

CPC classification number: G01M11/31 ,  B64C25/60 ,  G01F23/2922 ,  G01F23/2925 ,  G01F25/0061 ,  G01F25/0076 ,  G01M3/3245

Abstract: A system for monitoring a liquid level in an aircraft shock strut includes a cylinder having an internal chamber sealed by a piston telescopically movable within the cylinder. The chamber contains a gas and a liquid, and a sensor assembly is provided for monitoring a condition of a level of the liquid in the chamber. The sensor assembly includes at least one probe within the chamber, and a fitting assembly allows one or more leads from the probe to pass through the wall of the strut while maintaining pressure in the chamber. The fitting assembly includes a plug molded to the one or more leads extending from the probe. The fitting assembly also includes a retainer for holding the plug in sealed relationship with a through passage in the strut.

Abstract translation: 用于监测飞行器冲击支柱中的液位的系统包括具有由可在气缸内可伸缩移动的活塞密封的内部腔室的气缸。 所述腔室包含气体和液体，并且设置有用于监测腔室中液体水平的状态的传感器组件。 传感器组件包括腔室内的至少一个探针，并且接头组件允许来自探针的一个或多个引线穿过支柱的壁，同时保持腔室中的压力。 配件组件包括模制到从探针延伸的一个或多个引线的插头。 装配组件还包括用于将插头与支柱中的通道保持密封关系的保持器。