子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Takeoff/landing touchdown protection management system | US13488916 | 2012-06-05 | US09354635B2 | 2016-05-31 | Shyhpyng Jack Shue |
| An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states. | ||||||
| 82 | Landing gear electrical swivel | US14930956 | 2015-11-03 | US09315260B2 | 2016-04-19 | Derek C Milsom |
| An electrical swivel system may have a movable swivel member adapted to connect to a landing gear and a fixed swivel member adapted to connect to an airframe. Each may have an interface apparatus whereby electrical signals may be conducted between components of the movable swivel member and the fixed swivel member. In this manner, electrical signals may be conveyed across a mechanically movable joint. | ||||||
| 83 | DYNAMIC BEARING | US14785117 | 2014-04-03 | US20160084307A1 | 2016-03-24 | Ian Robert BENNETT |
| A dynamic bearing for an aircraft landing gear. The bearing includes a lug; a shaft having a first material; and a bearing surface having a second material that is softer than the first material. The bearing surface defines a bore and is arranged to support the shaft when the shaft is movably housed within the bore in use. The bearing surface is defined by the lug or a coating applied to the lug. | ||||||
| 84 | Nose landing gear arrangements and methods for making the same | US14201345 | 2014-03-07 | US09290263B2 | 2016-03-22 | Brian Cook; John Louis; Thomas Van de Ven; Robert M. Vieito; Mehdi R. Khorrami |
| Nose landing gear arrangements including a folding follow-up door for reducing airflow noise for aircrafts, aircrafts including such nose landing gear arrangements, and methods for making such nose landing gear arrangements are provided herein. In one example, a nose landing gear arrangement includes a wheel assembly and a main strut. The main strut is operatively coupled to the wheel assembly and is configured to extend outside of the fuselage substantially along a generally vertical plane. A folding follow-up door is pivotally coupled to the main strut and extends to the fuselage. The folding follow-up door includes a first door section and a second door section that extend outwardly in directions away from each other to define an unfolded position. The folding follow-up door is foldable to move the first and second door sections towards each other about the generally vertical plane to define a folded position. | ||||||
| 85 | LANDING GEAR ELECTRICAL SWIVEL | US14930956 | 2015-11-03 | US20160052622A1 | 2016-02-25 | Derek C. Milsom |
| An electrical swivel system may have a movable swivel member adapted to connect to a landing gear and a fixed swivel member adapted to connect to an airframe. Each may have an interface apparatus whereby electrical signals may be conducted between components of the movable swivel member and the fixed swivel member. In this manner, electrical signals may be conveyed across a mechanically movable joint. | ||||||
| 86 | METHOD OF DETECTING A LEAK PAST A DYNAMIC SEAL IN AIRCRAFT LANDING GEAR | US14789314 | 2015-07-01 | US20160009423A1 | 2016-01-14 | Graeme STEEL |
| A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20). | ||||||
| 87 | Splitter plate for aircraft noise reduction apparatus | US13680598 | 2012-11-19 | US09090333B2 | 2015-07-28 | Leung Choi Chow; Matthew Spiteri; Xin Zhang; David Angland; Michael Goodyer |
| An aircraft noise-reduction apparatus comprise a flow-facing element (1) and a flow control device (2) positioned downstream of the flow-facing element (1). The flow control device (2) is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element (1). | ||||||
| 88 | Configuring landing supports for landing on uneven terrain | US13644489 | 2012-10-04 | US09008872B2 | 2015-04-14 | William Peck Pflug; Charles Briggs Spinelli |
| A system for configuring landing supports of a load to land on uneven terrain includes a terrain sensor configured to detect a terrain characteristic of the uneven terrain. The system further includes landing supports configured to support the load upon landing. The system also includes a support control device operatively coupled to the landing supports, and a landing support control computer that is operatively coupled to the terrain sensor, landing supports, and support control device. The landing support control computer may determine if landing on the uneven terrain is allowable, based on the terrain characteristic and a load characteristic of the load. Upon determining that landing on the uneven terrain is allowable, the support control device configures the landing supports for landing on the uneven terrain. | ||||||
| 89 | Attachment bracket for landing gear | US13679464 | 2012-11-16 | US08979022B2 | 2015-03-17 | Michael Lee Custard |
| Attachment brackets are disclosed which are configured to be removably mounted on aircraft landing gear, e.g., by bolting the bracket to the landing gear. The attachment brackets may be used to secure skis, pontoons, or other landing equipment to the landing gear of the aircraft. In preferred implementations, the brackets are bolted on using existing factory drilled holes in the landing gear. | ||||||
| 90 | BOGIE BEAM ANGLE SENSOR | US13963663 | 2013-08-09 | US20150041585A1 | 2015-02-12 | Gary Holloway; James Acks |
| A bogie beam sensor may include a bracket and a target arm pivotably coupled to the bracket. The bracket may be coupled to a bogie beam. A sensor may be coupled to the bracket, and a target may be coupled to the target arm. A drive link may be coupled to the target arm and a piston. In response to the bogie beam pivoting with respect to the piston, the drive link may cause the target arm to rotate with respect to the bogie beam. The sensor may detect movement of the target on the target arm, and an angular position of the bogie beam may be determined based on the position of the target. | ||||||
| 91 | 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. | ||||||
| 92 | Motor for driving aircraft, located adjacent to undercarriage wheel | US13549520 | 2012-07-16 | US08820675B2 | 2014-09-02 | Isaiah W. Cox; Hans J. Walitzki; Jonathan Edelson |
| The invention disclosed is a self-propelled aircraft undercarriage for driving an aircraft on the ground, comprising: an axle; a strut supporting said axle; at least one wheel rotatably mounted on said axle; and drive means for driving said at least one wheel; characterized in that said drive means is disk shaped and is external to said wheel. In one embodiment of the invention, said drive means is mounted on said axle between said strut and said wheel. In a second embodiment, said drive means is mounted on said axle, on the side of said wheel furthest from said strut. | ||||||
| 93 | 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. | ||||||
| 94 | HOT EXTRUSION METHOD FOR PRODUCING A METAL PART, EXTRUSION TOOL FOR IMPLEMENTATION IT AND LANDING GEAR ROD THUS PRODUCED | US13825119 | 2012-05-04 | US20140053623A1 | 2014-02-27 | Laurent Hebrard |
| A hot extrusion method for producing a metal piece comprising a tubular portion whereof one of the two ends is extended by a complex shape is provided. The method comprises: heating a billet from which the piece is made; and transferring the billet into a press extrusion tool, the tool including a cavity where the billet is placed and the shape of which substantially corresponds to the outer shape of the piece. The metal has, cold, a flow stress equal to or above 200 MPa. The complex shape and tubular portion are made by the following successive steps: at least one direct extrusion step using the first punch to produce the complex shape; a step for replacing the first punch with a second punch on the tool; at least one reverse extrusion step in the same tool to produce the tubular portion; and a step for evacuating the extruded piece. | ||||||
| 95 | Attachment Bracket for Landing Gear | US13679464 | 2012-11-16 | US20140021296A1 | 2014-01-23 | Michael Lee Custard |
| Attachment brackets are disclosed which are configured to be removably mounted on aircraft landing gear, e.g., by bolting the bracket to the landing gear. The attachment brackets may be used to secure skis, pontoons, or other landing equipment to the landing gear of the aircraft. In preferred implementations, the brackets are bolted on using existing factory drilled holes in the landing gear. | ||||||
| 96 | Landing gear with noise reduction fairing | US12458407 | 2009-07-10 | US08490914B2 | 2013-07-23 | Leung Choi Chow; Philip Campbell; Christopher Wood; Andrew John Dyer |
| An aircraft noise reduction apparatus includes an aircraft landing gear assembly and a noise reduction fairing 12. The landing gear assembly includes a landing gear 10 arranged to be moveable between a stowed position and a fully deployed position. The noise reduction fairing 12 may include a wrap-around fairing which, when the landing gear 10 is in its fully deployed position, wraps around the landing gear 10 and extends along the majority of the length of a landing gear leg 11. A landing gear bay door assembly 16, 17 including at least one door may also be provided. The fairing 12 may have a recess 24 for accommodating one of landing gear bay doors when the door 16 is in its fully open position. | ||||||
| 97 | Motor for Driving Aircraft, Located Adjacent to Undercarriage Wheel | US13549520 | 2012-07-16 | US20130119190A1 | 2013-05-16 | Isaiah W. Cox; Hans J. Walitzki; Jonathan Edelson |
| The invention disclosed is a self-propelled aircraft undercarriage for driving an aircraft on the ground, comprising: an axle; a strut supporting said axle; at least one wheel rotatably mounted on said axle; and drive means for driving said at least one wheel; characterized in that said drive means is disk shaped and is external to said wheel. In one embodiment of the invention, said drive means is mounted on said axle between said strut and said wheel. In a second embodiment, said drive means is mounted on said axle, on the side of said wheel furthest from said strut. | ||||||
| 98 | METHOD FOR ADJUSTING THE DOORS OF A LANDING GEAR BAY, AND ASSOCIATED DOOR | US13808156 | 2011-07-05 | US20130099052A1 | 2013-04-25 | Gilbert Gleyze |
| The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension manoeuvres, by incorporating a specific entrance in the fairing (2) of the landing gear bay (4) that provides access to the different accessories (14, 17a, 17b) used to adjust the doors (21-25). The method of the invention consists in: providing a removable bodywork element (5) which is inserted into the fairing (2) of a landing gear bay, surrounded by a stiffening structure (7) and of sufficient dimension such that the adjustment levers (14, 17a, 17b) can be reached from the outside; accessing the inside of the bay (4) by retracting the removable bodywork element (5); and using the levers (14, 17a, 17b) to adjust the different doors (21 to 25) in a flush aerodynamic position, as well as the clearances between said doors. In one embodiment of the invention, one door (25) comprises a central bodywork portion (5) and a peripheral portion (7) including stiffening means (70). The peripheral portion (7) is surrounded by a seal (30) that bears on the other doors (21-24) via the stiffening means (70) and the central portion (5) is coupled to the peripheral portion (7) by removable separation means (6). | ||||||
| 99 | Means to improve the performance of high energy brakes such as in aircraft landing gear. | US13621844 | 2012-09-17 | US20130092787A1 | 2013-04-18 | Michal Polubinski |
| The invention provides means to prevent high-performance brakes from overheating by delivering coolant to the heat-generating brake components. As a result of implementing the invention, the brakes can then be used more effectively to control an aircraft during aborted landing after touchdown. After the aircraft completed the braking action, the risk of damaging tire explosions and undercarriage fires is minimized. The aircraft does not require an extensive post-incident overhaul and can be back in service much faster than when and if the invention is not implemented.Another component of the invention reduces the wear and tear of aircraft tires by providing self-propelled rotation before touchdown. | ||||||
| 100 | Torque link set | US12458242 | 2009-07-06 | US08371524B2 | 2013-02-12 | Leung Choi Chow; Philip Campbell; Christopher Neil Wood |
| An aircraft landing gear (10) includes a torque link set (12) comprising a first fairing (12a) rotatably connected at a first end (18) to a first end (19) of a second fairing (12b). The fairings (12a), (12b) may be arranged to act as first and second torque links. The fairings may be in the form of noise reduction fairings. | ||||||
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