Class / Patent application number | Description | Number of patent applications / Date published |
244103000 | Wheel | 53 |
20080251639 | Aircraft Wheel Assembly - A wheel assembly ( | 10-16-2008 |
20090206199 | DEBRIS DEFLECTING DEVICE, SYSTEM, AND METHOD - A debris deflector includes a bracket and a horizontal blade assembly. The bracket is to secure the debris deflector to an aft side of a landing gear assembly. The horizontal blade assembly is secured to the bracket. The horizontal blade assembly includes a blade and flap. The blade has a forward blade edge, blade body, and trailing blade edge. The forward blade edge is configured for placement aft of a tire for the landing gear assembly. The blade body extends outward from the forward blade edge substantially parallel to a road surface. The flap is secured to the trailing blade edge and extends from the trailing blade edge generally rearward and downward from the trailing edge. | 08-20-2009 |
20090294583 | AIRCRAFT LANDING GEAR ASSEMBLY SHIMMY DAMPER - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation. | 12-03-2009 |
20100001130 | Hybrid aircraft wheel having metal and composite portions - An aircraft wheel ( | 01-07-2010 |
20110001005 | LANDING GEAR LEGS AND METHOD OF MAKING - An airplane gear leg that is strong, stiff, and capable of storing large amounts of energy and formed of a composite material that has first and second fiber materials. The first fiber material is very strong and flexible, allowing it to store a great deal of energy in a hard landing, and its fibers are oriented essentially parallel to the axis of the gear leg. The second fiber material is very stiff, providing the torsional rigidity necessary to avoid flutter, and its stiff fibers are laid at a large angle relative to the axis of the gear leg so their elastic limit is not exceeded during a hard landing. | 01-06-2011 |
20110024558 | Ball wheel for an aircraft - A ball drive assembly for a vertical takeoff and land aircraft of the type having a plurality of supports extending outwardly from a central aircraft body. The ball drive assembly for one of the supports has a ball wheel housing containing a spherical, rigid ball, a drive shaft extending into the ball, a first driver for initiating rotating movement of the ball with respect to the ball wheel housing, and a second driver for initiating swiveling left and right movement of the ball so that it twists laterally of the ball wheel housing. Two motors are connected to the drivers, for operating them to rotate the ball with respect to the ball wheel housing, and effect both straight line movement and turning movement of the assembly. | 02-03-2011 |
20110297786 | Integrated Electric Motor and Gear in an Aircraft Wheel - A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a geared motor assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the geared motor assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle. | 12-08-2011 |
20120138742 | METHOD OF CONTROLLING A BRUSHLESS DC MOTOR - The invention relates to a method of powering at least one brushless DC electric motor having a plurality of phases for powering, the method including the steps of associating a static contactor with the motor for taking input voltage pulses and delivering polyphase voltage pulses to the motor in a manner that is servo-controlled to the angular position of the rotor of the motor, and for generating from a DC voltage source voltage pulses of frequency that is fixed and at a duty ratio that is controllable, thereby forming the input voltage pulses to the static contactor. | 06-07-2012 |
20120267477 | Valve stem access system for aircraft - A valve stem access system including a valve stem access assembly for an aircraft wheel cover is provided. One variation of the valve stem access system is designed for installation on a surface of an aircraft wheel fairing or pant and includes an installation template and positioning and cutting guide for accurate location and attachment of a valve stem access assembly that provides easy access to the aircraft wheel tire valve stem through a movable access panel. An alignment and indicator guide provides visual confirmation that the valve stem is correctly aligned with the access assembly. In another variation, a valve stem access assembly for an aircraft wheel hub cover is also provided. | 10-25-2012 |
20130001358 | GREASE BAFFLE SYSTEM - The present invention provides for a grease baffle that may be installed and removed independently of an outer race of a bearing assembly, thus reducing or eliminating damage to the grease baffle during maintenance actions. Further, the present invention eliminates the potential for damage to the bearing support body for maintenance actions requiring removal of the grease baffle but not removal of the outer race. Moreover, the present invention results in reduced maintenance time and reduced maintenance costs. The grease baffle may be retained in the support body by a retaining ring or a resilient sealing member, and may be preloaded against a retaining surface. | 01-03-2013 |
20130062466 | MOTOR AND GEARING SYSTEM FOR AIRCRAFT WHEEL - A compact in-wheel vehicle motor and gearing system designed to meet high power and torque requirements for driving a vehicle on the ground independently of other power sources is provided. The motor and gearing system includes a motor assembly with an outside rotor element mounted for rotation about an inside stator element and a gear assembly with a plurality of gear stages mounted inside the stator and drivingly connected to the motor assembly. The motor assembly and gear assembly are mounted interiorly of the wheel and completely within a space defined by the internal dimensions of the wheel. This motor and gearing system can be effectively installed in an existing aircraft wheel without changes to other components to produce a drive wheel with the torque and power required to move the aircraft independently on the ground. | 03-14-2013 |
20130233969 | MOVABLE BUSHING INTERFACE AND TAXI DRIVE SYSTEM - A drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure. | 09-12-2013 |
20140027571 | CONTROLLED LANDING GEAR TIRE TRACTION SYSTEM - A landing gear tire traction control system and methods are presented. An outer tire of an aircraft wheel is depressurized to a depressurized state in response to a non-optimal aircraft landing condition. An inner rotor of the aircraft wheel contacts the outer tire in response to the depressurized state, and a plurality of traction studs are deployed to protrude from the outer tire in response to the inner rotor contacting the outer tire. | 01-30-2014 |
20140239121 | AIRCRAFT LANDING GEAR COOLING SYSTEM - According to one embodiment, an apparatus for cooling at least one landing gear brake of an aircraft in flight is described. The apparatus includes an air handling assembly that is coupled to the aircraft. The air handling assembly includes at least one air inlet port. The apparatus also includes an air delivery assembly that is in air receiving communication with the air handling assembly. The air delivery assembly includes at least one nozzle that is configured to direct air into a first space adjacent a first side of the landing gear brake to create an air pressure differential across the landing gear brake. | 08-28-2014 |
20140374538 | AIRCRAFT LANDING GEAR - An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition. | 12-25-2014 |
20150021434 | SELF-ORIENTING AIRCRAFT LANDING GEAR - An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage. | 01-22-2015 |
20150136902 | AIRCRAFT BRAKE ASSEMBLY - An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground. | 05-21-2015 |
20150314859 | AIRCRAFT UNDERCARRIAGE LEG INCLUDING A UNIT FOR DRIVING THE WHEELS - Aircraft undercarriage leg including an axle ( | 11-05-2015 |
20160009381 | SYSTEM FOR FAST FIXING AN ACCESSORY TO A DRONE BODY | 01-14-2016 |
20160009382 | SELF-ORIENTING AIRCRAFT LANDING GEAR | 01-14-2016 |
20160052624 | Method of Operating Aircraft Drive To Move an Aircraft Under Adverse Ground Conditions - A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed. | 02-25-2016 |
20160090173 | AIRCRAFT LANDING GEAR - An aircraft landing gear comprising an axle ( | 03-31-2016 |
20160096619 | AIRCRAFT UNDERCARRIAGE - An undercarriage comprising at least:
| 04-07-2016 |
20160101847 | NOSE WHEEL STEERING - A nose wheel steering mechanism comprises a first, rotationally fixed nose wheel leg portion and a second, rotatable nose wheel leg portion arranged at least partially within and extending parallel to the first nose wheel leg portion. A toroidal electric motor is mounted to and extends around the first nose wheel leg portion. Toroidal gearing is mounted to and extends around the first nose wheel leg and has an input driven by the toroidal electric motor and an output coupled to and driving the second nose wheel leg portion. | 04-14-2016 |
20160107747 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut. | 04-21-2016 |
20160144982 | UAV DOCKING SYSTEM AND METHOD - An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle. | 05-26-2016 |
20160159469 | METHOD FOR USING AIRCRAFT WHEEL TYRE PRESSURE TO IMPROVE AIRCRAFT ENERGY EFFICIENCY AND DRIVE SYSTEM PERFORMANCE - A method for improving both drive system performance and energy efficiency performance both in an aircraft equipped with one or more drive wheel drive systems to move the aircraft autonomously on the ground is provided and in an aircraft that relies on its engines for ground movement. Achieving these objectives takes advantage of a discovered relationship between aircraft tyre pressure, drive system performance, and energy efficiency. Monitoring and maintaining tyre inflation pressure of an aircraft's tyres at an inflation level near a high end or recommended maximum cold or hot operating pressure for a specific kind of aircraft tyre on a specific aircraft not only improves drive wheel drive system performance, but also substantially and significantly improves energy efficiency in all types of aircraft. | 06-09-2016 |
20160167771 | DEVICE FOR MOUNTING AN AIRCRAFT TAIL WHEEL | 06-16-2016 |
20160169762 | COMBINATION TIRE PRESSURE SENSOR AND OVER-INFLATION PRESSURE RELIEF VALVE | 06-16-2016 |
20120305704 | CONTROL DEVICE FOR AIRCRAFT - The invention relates to a control device for aircraft comprising at least one aircraft undercarriage | 12-06-2012 |
20130112809 | Apparatus for Pre-Rotating Aircraft Tires - A disc-shaped accessory having radially-hinged flaps is adapted to be attached to an aircraft wheel. The flaps open no more than 90° (preferably 45-70°) in an airstream to exert a rotational torque on the wheel, causing the wheel to spin. The rotation helps reduce tire wear and damage during aircraft landing. | 05-09-2013 |
20140048648 | Free Spinning Wheel for Airplanes - The landing gear wheels of an aircraft include modified tires mounted on the rim of the wheel include a plurality of fins integral with the sidewall of the tires and configured to catch the wind created by movement of the aircraft through the air for spinning the wheel in a forward motion direction when the landing gear has been deployed and before the aircraft touches down, thereby reducing the friction between the runway and the tire upon touchdown. | 02-20-2014 |
20150021435 | Apparatus for causing an aircraft wheel to rotate - A rotator assembly for rotating an aircraft landing wheel by the action of the airstream flowing thereby has a circular plate mounted on the wheel and a plurality of independently movable cone shape connected to the outer surface of the plate in circumferentially spaced relation. Each cone shape member has a circle leading edge facing generally in the direction in which the wheel is to be rotated. As the wheel rotates, the members, which were previously pivoted outward, become engaged by the airstream and are sequentially forced inward against the plate. | 01-22-2015 |
20150314862 | WHEEL MOTORIZING SYSTEM, NOTABLY FOR AN AIRCRAFT WHEEL - Wheel motorization system, notably for an aircraft running along the ground, comprising an electric motor ( | 11-05-2015 |
20150329202 | CONTROL OF GROUND TRAVEL AND STEERING IN AN AIRCRAFT WITH POWERED MAIN GEAR DRIVE WHEELS - A controllable aircraft taxi system is provided that enables the simultaneous control of aircraft autonomous ground movement and direction of aircraft autonomous ground movement. Independently controlled non-engine drive means capable of driving an aircraft landing gear wheel to move an aircraft autonomously on the ground without reliance on the aircraft's main engines are mounted to provide driving torque to aircraft a selected number of main landing gear wheels. The aircraft nose landing gear steering system is provided with steering angle detection and measurement means adapted to communicate with main landing gear wheel non-engine drive means, enabling simultaneous control over both autonomous aircraft ground travel and direction of autonomous aircraft ground travel. The present invention overcomes steering challenges presented by using non-engine drive means on main landing gear wheels to drive aircraft autonomously during taxi. | 11-19-2015 |
20160039519 | LANDING GEAR DRIVE SYSTEM - The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion. | 02-11-2016 |
20160176516 | AIRCRAFT LANDING GEAR | 06-23-2016 |
20160194077 | SPACE-MAXIMIZING CLUTCH ARRANGEMENT FOR VEHICLE DRIVE WHEEL | 07-07-2016 |
20160200424 | TIRE SPINNING ASSEMBLY | 07-14-2016 |
244104000 | Resiliently mounted | 14 |
20090152396 | Aircraft Landing Gear Assembly Shimmy Damper - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. An elastomer encompasses the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. | 06-18-2009 |
20110155848 | AIRCRAFT UNDERCARRIAGE HAVING A ROCKER LEVER WITH A SWIVEL AND A HINGED TWIN WHEELS - The invention relates to an aircraft undercarriage ( | 06-30-2011 |
20120043419 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly comprising an impact protection boot mounted to a landing gear component, the impact protection boot comprising: a resilient inner impact energy absorption layer which engages the component; and an outer protective layer which substantially covers the impact energy absorption layer, wherein the inner layer is more compressible than the outer layer. The boot has first and second ends which are tied to each other by a connector which exerts oppositely directed forces on the first and second ends respectively, the forces being directed around the circumference of the boot so as to tighten the boot against the landing gear component. | 02-23-2012 |
20120234972 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +α and −α with respect to a longitudinal axis of the leg, where α is between 2 and 8 degrees. | 09-20-2012 |
20150375856 | PITCH TRIMMER ACTUATOR WITH VARIABLE DAMPING - A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements. | 12-31-2015 |
20100133379 | Landing gear strut extender - A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely affecting its spring rate while the ability to withdraw fluid from a strut maintains the ability of the strut to absorb the impact of landing. The mechanism is readily retrofitable to existing landing gear systems to accommodate more efficient under the wing intake designs and to reduce the likelihood of FOD during taxiing at minimal cost and with very a minimal increase in the aircraft weight. | 06-03-2010 |
20100181423 | AIRCRAFT SHOCK STRUT HAVING FIXED UPPER BEARING - An aircraft shock strut includes a cylinder and a piston movable within the cylinder. A lower bearing and an upper bearing provide sliding engagement between the cylinder and the piston. The upper bearing is fixed to the cylinder and provides sliding engagement with an outer surface the piston. An upper bearing that is fixed to the cylinder facilitates use of lighter weight materials for the cylinder without sacrificing durability. | 07-22-2010 |
20100187353 | SHOCK-ABSORBER FOR AIRCRAFT LANDING GEAR - The invention relates to a shock-absorber for aircraft landing gear, the shock-absorber having two elements ( | 07-29-2010 |
20100288878 | LOAD DETECTION IN AN AIRCRAFT LANDING GEAR - A landing gear for an aircraft includes a shock absorber strut ( | 11-18-2010 |
20110260001 | LANDING GEAR PROVIDED WITH ENERGY ABSORBER MEANS, AN AIRCRAFT PROVIDED WITH SAID LANDING GEAR, AND A METHOD OF LANDING - Aircraft landing gear ( | 10-27-2011 |
20120126055 | HYDRAULIC ACTUATOR FOR SEMI LEVERED LANDING GEAR - A device including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons. | 05-24-2012 |
20130140399 | MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS AND A DEFORMABLE PARALLELOGRAM STRUCTURE - An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system. | 06-06-2013 |
20190144105 | CENTER BIASED ACTUATOR | 05-16-2019 |
20090277992 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. The composite leg further includes a torque box including carbon reinforcing fibers for providing torsional rigidity of the leg and carrying shear flow between the caps. The carbon fibers in the torque box are oriented at +θ and −θ with respect to a longitudinal axis of the leg, where θ is between 35 and 55 degrees. | 11-12-2009 |
244104000 | Fluid pressure | 8 |
20090152396 | Aircraft Landing Gear Assembly Shimmy Damper - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. An elastomer encompasses the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. | 06-18-2009 |
20110155848 | AIRCRAFT UNDERCARRIAGE HAVING A ROCKER LEVER WITH A SWIVEL AND A HINGED TWIN WHEELS - The invention relates to an aircraft undercarriage ( | 06-30-2011 |
20120043419 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly comprising an impact protection boot mounted to a landing gear component, the impact protection boot comprising: a resilient inner impact energy absorption layer which engages the component; and an outer protective layer which substantially covers the impact energy absorption layer, wherein the inner layer is more compressible than the outer layer. The boot has first and second ends which are tied to each other by a connector which exerts oppositely directed forces on the first and second ends respectively, the forces being directed around the circumference of the boot so as to tighten the boot against the landing gear component. | 02-23-2012 |
20120234972 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +α and −α with respect to a longitudinal axis of the leg, where α is between 2 and 8 degrees. | 09-20-2012 |
20150375856 | PITCH TRIMMER ACTUATOR WITH VARIABLE DAMPING - A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements. | 12-31-2015 |
20100133379 | Landing gear strut extender - A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely affecting its spring rate while the ability to withdraw fluid from a strut maintains the ability of the strut to absorb the impact of landing. The mechanism is readily retrofitable to existing landing gear systems to accommodate more efficient under the wing intake designs and to reduce the likelihood of FOD during taxiing at minimal cost and with very a minimal increase in the aircraft weight. | 06-03-2010 |
20100181423 | AIRCRAFT SHOCK STRUT HAVING FIXED UPPER BEARING - An aircraft shock strut includes a cylinder and a piston movable within the cylinder. A lower bearing and an upper bearing provide sliding engagement between the cylinder and the piston. The upper bearing is fixed to the cylinder and provides sliding engagement with an outer surface the piston. An upper bearing that is fixed to the cylinder facilitates use of lighter weight materials for the cylinder without sacrificing durability. | 07-22-2010 |
20100187353 | SHOCK-ABSORBER FOR AIRCRAFT LANDING GEAR - The invention relates to a shock-absorber for aircraft landing gear, the shock-absorber having two elements ( | 07-29-2010 |
20100288878 | LOAD DETECTION IN AN AIRCRAFT LANDING GEAR - A landing gear for an aircraft includes a shock absorber strut ( | 11-18-2010 |
20110260001 | LANDING GEAR PROVIDED WITH ENERGY ABSORBER MEANS, AN AIRCRAFT PROVIDED WITH SAID LANDING GEAR, AND A METHOD OF LANDING - Aircraft landing gear ( | 10-27-2011 |
20120126055 | HYDRAULIC ACTUATOR FOR SEMI LEVERED LANDING GEAR - A device including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons. | 05-24-2012 |
20130140399 | MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS AND A DEFORMABLE PARALLELOGRAM STRUCTURE - An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system. | 06-06-2013 |
20190144105 | CENTER BIASED ACTUATOR | 05-16-2019 |
20090277992 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. The composite leg further includes a torque box including carbon reinforcing fibers for providing torsional rigidity of the leg and carrying shear flow between the caps. The carbon fibers in the torque box are oriented at +θ and −θ with respect to a longitudinal axis of the leg, where θ is between 35 and 55 degrees. | 11-12-2009 |
244104000 | Leaf spring | 1 |
20090152396 | Aircraft Landing Gear Assembly Shimmy Damper - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. An elastomer encompasses the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. | 06-18-2009 |
20110155848 | AIRCRAFT UNDERCARRIAGE HAVING A ROCKER LEVER WITH A SWIVEL AND A HINGED TWIN WHEELS - The invention relates to an aircraft undercarriage ( | 06-30-2011 |
20120043419 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly comprising an impact protection boot mounted to a landing gear component, the impact protection boot comprising: a resilient inner impact energy absorption layer which engages the component; and an outer protective layer which substantially covers the impact energy absorption layer, wherein the inner layer is more compressible than the outer layer. The boot has first and second ends which are tied to each other by a connector which exerts oppositely directed forces on the first and second ends respectively, the forces being directed around the circumference of the boot so as to tighten the boot against the landing gear component. | 02-23-2012 |
20120234972 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +α and −α with respect to a longitudinal axis of the leg, where α is between 2 and 8 degrees. | 09-20-2012 |
20150375856 | PITCH TRIMMER ACTUATOR WITH VARIABLE DAMPING - A pitch trimmer assembly for an aircraft landing gear having a damping element arranged to be connected between a first and a second element of an aircraft landing gear and arranged to exert a first damping force when in a first state and a second damping force in a second state, the damping element being switchable between the first and second states in dependence on the relative positions of the first and second landing gear elements. | 12-31-2015 |
20100133379 | Landing gear strut extender - A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely affecting its spring rate while the ability to withdraw fluid from a strut maintains the ability of the strut to absorb the impact of landing. The mechanism is readily retrofitable to existing landing gear systems to accommodate more efficient under the wing intake designs and to reduce the likelihood of FOD during taxiing at minimal cost and with very a minimal increase in the aircraft weight. | 06-03-2010 |
20100181423 | AIRCRAFT SHOCK STRUT HAVING FIXED UPPER BEARING - An aircraft shock strut includes a cylinder and a piston movable within the cylinder. A lower bearing and an upper bearing provide sliding engagement between the cylinder and the piston. The upper bearing is fixed to the cylinder and provides sliding engagement with an outer surface the piston. An upper bearing that is fixed to the cylinder facilitates use of lighter weight materials for the cylinder without sacrificing durability. | 07-22-2010 |
20100187353 | SHOCK-ABSORBER FOR AIRCRAFT LANDING GEAR - The invention relates to a shock-absorber for aircraft landing gear, the shock-absorber having two elements ( | 07-29-2010 |
20100288878 | LOAD DETECTION IN AN AIRCRAFT LANDING GEAR - A landing gear for an aircraft includes a shock absorber strut ( | 11-18-2010 |
20110260001 | LANDING GEAR PROVIDED WITH ENERGY ABSORBER MEANS, AN AIRCRAFT PROVIDED WITH SAID LANDING GEAR, AND A METHOD OF LANDING - Aircraft landing gear ( | 10-27-2011 |
20120126055 | HYDRAULIC ACTUATOR FOR SEMI LEVERED LANDING GEAR - A device including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons. | 05-24-2012 |
20130140399 | MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS AND A DEFORMABLE PARALLELOGRAM STRUCTURE - An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system. | 06-06-2013 |
20190144105 | CENTER BIASED ACTUATOR | 05-16-2019 |
20090277992 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. The composite leg further includes a torque box including carbon reinforcing fibers for providing torsional rigidity of the leg and carrying shear flow between the caps. The carbon fibers in the torque box are oriented at +θ and −θ with respect to a longitudinal axis of the leg, where θ is between 35 and 55 degrees. | 11-12-2009 |
244103000 | Prerotation | 9 |
20080251639 | Aircraft Wheel Assembly - A wheel assembly ( | 10-16-2008 |
20090206199 | DEBRIS DEFLECTING DEVICE, SYSTEM, AND METHOD - A debris deflector includes a bracket and a horizontal blade assembly. The bracket is to secure the debris deflector to an aft side of a landing gear assembly. The horizontal blade assembly is secured to the bracket. The horizontal blade assembly includes a blade and flap. The blade has a forward blade edge, blade body, and trailing blade edge. The forward blade edge is configured for placement aft of a tire for the landing gear assembly. The blade body extends outward from the forward blade edge substantially parallel to a road surface. The flap is secured to the trailing blade edge and extends from the trailing blade edge generally rearward and downward from the trailing edge. | 08-20-2009 |
20090294583 | AIRCRAFT LANDING GEAR ASSEMBLY SHIMMY DAMPER - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation. | 12-03-2009 |
20100001130 | Hybrid aircraft wheel having metal and composite portions - An aircraft wheel ( | 01-07-2010 |
20110001005 | LANDING GEAR LEGS AND METHOD OF MAKING - An airplane gear leg that is strong, stiff, and capable of storing large amounts of energy and formed of a composite material that has first and second fiber materials. The first fiber material is very strong and flexible, allowing it to store a great deal of energy in a hard landing, and its fibers are oriented essentially parallel to the axis of the gear leg. The second fiber material is very stiff, providing the torsional rigidity necessary to avoid flutter, and its stiff fibers are laid at a large angle relative to the axis of the gear leg so their elastic limit is not exceeded during a hard landing. | 01-06-2011 |
20110024558 | Ball wheel for an aircraft - A ball drive assembly for a vertical takeoff and land aircraft of the type having a plurality of supports extending outwardly from a central aircraft body. The ball drive assembly for one of the supports has a ball wheel housing containing a spherical, rigid ball, a drive shaft extending into the ball, a first driver for initiating rotating movement of the ball with respect to the ball wheel housing, and a second driver for initiating swiveling left and right movement of the ball so that it twists laterally of the ball wheel housing. Two motors are connected to the drivers, for operating them to rotate the ball with respect to the ball wheel housing, and effect both straight line movement and turning movement of the assembly. | 02-03-2011 |
20110297786 | Integrated Electric Motor and Gear in an Aircraft Wheel - A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a geared motor assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the geared motor assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle. | 12-08-2011 |
20120138742 | METHOD OF CONTROLLING A BRUSHLESS DC MOTOR - The invention relates to a method of powering at least one brushless DC electric motor having a plurality of phases for powering, the method including the steps of associating a static contactor with the motor for taking input voltage pulses and delivering polyphase voltage pulses to the motor in a manner that is servo-controlled to the angular position of the rotor of the motor, and for generating from a DC voltage source voltage pulses of frequency that is fixed and at a duty ratio that is controllable, thereby forming the input voltage pulses to the static contactor. | 06-07-2012 |
20120267477 | Valve stem access system for aircraft - A valve stem access system including a valve stem access assembly for an aircraft wheel cover is provided. One variation of the valve stem access system is designed for installation on a surface of an aircraft wheel fairing or pant and includes an installation template and positioning and cutting guide for accurate location and attachment of a valve stem access assembly that provides easy access to the aircraft wheel tire valve stem through a movable access panel. An alignment and indicator guide provides visual confirmation that the valve stem is correctly aligned with the access assembly. In another variation, a valve stem access assembly for an aircraft wheel hub cover is also provided. | 10-25-2012 |
20130001358 | GREASE BAFFLE SYSTEM - The present invention provides for a grease baffle that may be installed and removed independently of an outer race of a bearing assembly, thus reducing or eliminating damage to the grease baffle during maintenance actions. Further, the present invention eliminates the potential for damage to the bearing support body for maintenance actions requiring removal of the grease baffle but not removal of the outer race. Moreover, the present invention results in reduced maintenance time and reduced maintenance costs. The grease baffle may be retained in the support body by a retaining ring or a resilient sealing member, and may be preloaded against a retaining surface. | 01-03-2013 |
20130062466 | MOTOR AND GEARING SYSTEM FOR AIRCRAFT WHEEL - A compact in-wheel vehicle motor and gearing system designed to meet high power and torque requirements for driving a vehicle on the ground independently of other power sources is provided. The motor and gearing system includes a motor assembly with an outside rotor element mounted for rotation about an inside stator element and a gear assembly with a plurality of gear stages mounted inside the stator and drivingly connected to the motor assembly. The motor assembly and gear assembly are mounted interiorly of the wheel and completely within a space defined by the internal dimensions of the wheel. This motor and gearing system can be effectively installed in an existing aircraft wheel without changes to other components to produce a drive wheel with the torque and power required to move the aircraft independently on the ground. | 03-14-2013 |
20130233969 | MOVABLE BUSHING INTERFACE AND TAXI DRIVE SYSTEM - A drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure. | 09-12-2013 |
20140027571 | CONTROLLED LANDING GEAR TIRE TRACTION SYSTEM - A landing gear tire traction control system and methods are presented. An outer tire of an aircraft wheel is depressurized to a depressurized state in response to a non-optimal aircraft landing condition. An inner rotor of the aircraft wheel contacts the outer tire in response to the depressurized state, and a plurality of traction studs are deployed to protrude from the outer tire in response to the inner rotor contacting the outer tire. | 01-30-2014 |
20140239121 | AIRCRAFT LANDING GEAR COOLING SYSTEM - According to one embodiment, an apparatus for cooling at least one landing gear brake of an aircraft in flight is described. The apparatus includes an air handling assembly that is coupled to the aircraft. The air handling assembly includes at least one air inlet port. The apparatus also includes an air delivery assembly that is in air receiving communication with the air handling assembly. The air delivery assembly includes at least one nozzle that is configured to direct air into a first space adjacent a first side of the landing gear brake to create an air pressure differential across the landing gear brake. | 08-28-2014 |
20140374538 | AIRCRAFT LANDING GEAR - An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition. | 12-25-2014 |
20150021434 | SELF-ORIENTING AIRCRAFT LANDING GEAR - An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage. | 01-22-2015 |
20150136902 | AIRCRAFT BRAKE ASSEMBLY - An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground. | 05-21-2015 |
20150314859 | AIRCRAFT UNDERCARRIAGE LEG INCLUDING A UNIT FOR DRIVING THE WHEELS - Aircraft undercarriage leg including an axle ( | 11-05-2015 |
20160009381 | SYSTEM FOR FAST FIXING AN ACCESSORY TO A DRONE BODY | 01-14-2016 |
20160009382 | SELF-ORIENTING AIRCRAFT LANDING GEAR | 01-14-2016 |
20160052624 | Method of Operating Aircraft Drive To Move an Aircraft Under Adverse Ground Conditions - A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed. | 02-25-2016 |
20160090173 | AIRCRAFT LANDING GEAR - An aircraft landing gear comprising an axle ( | 03-31-2016 |
20160096619 | AIRCRAFT UNDERCARRIAGE - An undercarriage comprising at least:
| 04-07-2016 |
20160101847 | NOSE WHEEL STEERING - A nose wheel steering mechanism comprises a first, rotationally fixed nose wheel leg portion and a second, rotatable nose wheel leg portion arranged at least partially within and extending parallel to the first nose wheel leg portion. A toroidal electric motor is mounted to and extends around the first nose wheel leg portion. Toroidal gearing is mounted to and extends around the first nose wheel leg and has an input driven by the toroidal electric motor and an output coupled to and driving the second nose wheel leg portion. | 04-14-2016 |
20160107747 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut. | 04-21-2016 |
20160144982 | UAV DOCKING SYSTEM AND METHOD - An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle. | 05-26-2016 |
20160159469 | METHOD FOR USING AIRCRAFT WHEEL TYRE PRESSURE TO IMPROVE AIRCRAFT ENERGY EFFICIENCY AND DRIVE SYSTEM PERFORMANCE - A method for improving both drive system performance and energy efficiency performance both in an aircraft equipped with one or more drive wheel drive systems to move the aircraft autonomously on the ground is provided and in an aircraft that relies on its engines for ground movement. Achieving these objectives takes advantage of a discovered relationship between aircraft tyre pressure, drive system performance, and energy efficiency. Monitoring and maintaining tyre inflation pressure of an aircraft's tyres at an inflation level near a high end or recommended maximum cold or hot operating pressure for a specific kind of aircraft tyre on a specific aircraft not only improves drive wheel drive system performance, but also substantially and significantly improves energy efficiency in all types of aircraft. | 06-09-2016 |
20160167771 | DEVICE FOR MOUNTING AN AIRCRAFT TAIL WHEEL | 06-16-2016 |
20160169762 | COMBINATION TIRE PRESSURE SENSOR AND OVER-INFLATION PRESSURE RELIEF VALVE | 06-16-2016 |
20120305704 | CONTROL DEVICE FOR AIRCRAFT - The invention relates to a control device for aircraft comprising at least one aircraft undercarriage | 12-06-2012 |
20130112809 | Apparatus for Pre-Rotating Aircraft Tires - A disc-shaped accessory having radially-hinged flaps is adapted to be attached to an aircraft wheel. The flaps open no more than 90° (preferably 45-70°) in an airstream to exert a rotational torque on the wheel, causing the wheel to spin. The rotation helps reduce tire wear and damage during aircraft landing. | 05-09-2013 |
20140048648 | Free Spinning Wheel for Airplanes - The landing gear wheels of an aircraft include modified tires mounted on the rim of the wheel include a plurality of fins integral with the sidewall of the tires and configured to catch the wind created by movement of the aircraft through the air for spinning the wheel in a forward motion direction when the landing gear has been deployed and before the aircraft touches down, thereby reducing the friction between the runway and the tire upon touchdown. | 02-20-2014 |
20150021435 | Apparatus for causing an aircraft wheel to rotate - A rotator assembly for rotating an aircraft landing wheel by the action of the airstream flowing thereby has a circular plate mounted on the wheel and a plurality of independently movable cone shape connected to the outer surface of the plate in circumferentially spaced relation. Each cone shape member has a circle leading edge facing generally in the direction in which the wheel is to be rotated. As the wheel rotates, the members, which were previously pivoted outward, become engaged by the airstream and are sequentially forced inward against the plate. | 01-22-2015 |
20150314862 | WHEEL MOTORIZING SYSTEM, NOTABLY FOR AN AIRCRAFT WHEEL - Wheel motorization system, notably for an aircraft running along the ground, comprising an electric motor ( | 11-05-2015 |
20150329202 | CONTROL OF GROUND TRAVEL AND STEERING IN AN AIRCRAFT WITH POWERED MAIN GEAR DRIVE WHEELS - A controllable aircraft taxi system is provided that enables the simultaneous control of aircraft autonomous ground movement and direction of aircraft autonomous ground movement. Independently controlled non-engine drive means capable of driving an aircraft landing gear wheel to move an aircraft autonomously on the ground without reliance on the aircraft's main engines are mounted to provide driving torque to aircraft a selected number of main landing gear wheels. The aircraft nose landing gear steering system is provided with steering angle detection and measurement means adapted to communicate with main landing gear wheel non-engine drive means, enabling simultaneous control over both autonomous aircraft ground travel and direction of autonomous aircraft ground travel. The present invention overcomes steering challenges presented by using non-engine drive means on main landing gear wheels to drive aircraft autonomously during taxi. | 11-19-2015 |
20160039519 | LANDING GEAR DRIVE SYSTEM - The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion. | 02-11-2016 |
20160176516 | AIRCRAFT LANDING GEAR | 06-23-2016 |
20160194077 | SPACE-MAXIMIZING CLUTCH ARRANGEMENT FOR VEHICLE DRIVE WHEEL | 07-07-2016 |
20160200424 | TIRE SPINNING ASSEMBLY | 07-14-2016 |
244103000 | Crosswind gear | 1 |
20080251639 | Aircraft Wheel Assembly - A wheel assembly ( | 10-16-2008 |
20090206199 | DEBRIS DEFLECTING DEVICE, SYSTEM, AND METHOD - A debris deflector includes a bracket and a horizontal blade assembly. The bracket is to secure the debris deflector to an aft side of a landing gear assembly. The horizontal blade assembly is secured to the bracket. The horizontal blade assembly includes a blade and flap. The blade has a forward blade edge, blade body, and trailing blade edge. The forward blade edge is configured for placement aft of a tire for the landing gear assembly. The blade body extends outward from the forward blade edge substantially parallel to a road surface. The flap is secured to the trailing blade edge and extends from the trailing blade edge generally rearward and downward from the trailing edge. | 08-20-2009 |
20090294583 | AIRCRAFT LANDING GEAR ASSEMBLY SHIMMY DAMPER - An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation. | 12-03-2009 |
20100001130 | Hybrid aircraft wheel having metal and composite portions - An aircraft wheel ( | 01-07-2010 |
20110001005 | LANDING GEAR LEGS AND METHOD OF MAKING - An airplane gear leg that is strong, stiff, and capable of storing large amounts of energy and formed of a composite material that has first and second fiber materials. The first fiber material is very strong and flexible, allowing it to store a great deal of energy in a hard landing, and its fibers are oriented essentially parallel to the axis of the gear leg. The second fiber material is very stiff, providing the torsional rigidity necessary to avoid flutter, and its stiff fibers are laid at a large angle relative to the axis of the gear leg so their elastic limit is not exceeded during a hard landing. | 01-06-2011 |
20110024558 | Ball wheel for an aircraft - A ball drive assembly for a vertical takeoff and land aircraft of the type having a plurality of supports extending outwardly from a central aircraft body. The ball drive assembly for one of the supports has a ball wheel housing containing a spherical, rigid ball, a drive shaft extending into the ball, a first driver for initiating rotating movement of the ball with respect to the ball wheel housing, and a second driver for initiating swiveling left and right movement of the ball so that it twists laterally of the ball wheel housing. Two motors are connected to the drivers, for operating them to rotate the ball with respect to the ball wheel housing, and effect both straight line movement and turning movement of the assembly. | 02-03-2011 |
20110297786 | Integrated Electric Motor and Gear in an Aircraft Wheel - A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a geared motor assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the geared motor assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle. | 12-08-2011 |
20120138742 | METHOD OF CONTROLLING A BRUSHLESS DC MOTOR - The invention relates to a method of powering at least one brushless DC electric motor having a plurality of phases for powering, the method including the steps of associating a static contactor with the motor for taking input voltage pulses and delivering polyphase voltage pulses to the motor in a manner that is servo-controlled to the angular position of the rotor of the motor, and for generating from a DC voltage source voltage pulses of frequency that is fixed and at a duty ratio that is controllable, thereby forming the input voltage pulses to the static contactor. | 06-07-2012 |
20120267477 | Valve stem access system for aircraft - A valve stem access system including a valve stem access assembly for an aircraft wheel cover is provided. One variation of the valve stem access system is designed for installation on a surface of an aircraft wheel fairing or pant and includes an installation template and positioning and cutting guide for accurate location and attachment of a valve stem access assembly that provides easy access to the aircraft wheel tire valve stem through a movable access panel. An alignment and indicator guide provides visual confirmation that the valve stem is correctly aligned with the access assembly. In another variation, a valve stem access assembly for an aircraft wheel hub cover is also provided. | 10-25-2012 |
20130001358 | GREASE BAFFLE SYSTEM - The present invention provides for a grease baffle that may be installed and removed independently of an outer race of a bearing assembly, thus reducing or eliminating damage to the grease baffle during maintenance actions. Further, the present invention eliminates the potential for damage to the bearing support body for maintenance actions requiring removal of the grease baffle but not removal of the outer race. Moreover, the present invention results in reduced maintenance time and reduced maintenance costs. The grease baffle may be retained in the support body by a retaining ring or a resilient sealing member, and may be preloaded against a retaining surface. | 01-03-2013 |
20130062466 | MOTOR AND GEARING SYSTEM FOR AIRCRAFT WHEEL - A compact in-wheel vehicle motor and gearing system designed to meet high power and torque requirements for driving a vehicle on the ground independently of other power sources is provided. The motor and gearing system includes a motor assembly with an outside rotor element mounted for rotation about an inside stator element and a gear assembly with a plurality of gear stages mounted inside the stator and drivingly connected to the motor assembly. The motor assembly and gear assembly are mounted interiorly of the wheel and completely within a space defined by the internal dimensions of the wheel. This motor and gearing system can be effectively installed in an existing aircraft wheel without changes to other components to produce a drive wheel with the torque and power required to move the aircraft independently on the ground. | 03-14-2013 |
20130233969 | MOVABLE BUSHING INTERFACE AND TAXI DRIVE SYSTEM - A drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure. | 09-12-2013 |
20140027571 | CONTROLLED LANDING GEAR TIRE TRACTION SYSTEM - A landing gear tire traction control system and methods are presented. An outer tire of an aircraft wheel is depressurized to a depressurized state in response to a non-optimal aircraft landing condition. An inner rotor of the aircraft wheel contacts the outer tire in response to the depressurized state, and a plurality of traction studs are deployed to protrude from the outer tire in response to the inner rotor contacting the outer tire. | 01-30-2014 |
20140239121 | AIRCRAFT LANDING GEAR COOLING SYSTEM - According to one embodiment, an apparatus for cooling at least one landing gear brake of an aircraft in flight is described. The apparatus includes an air handling assembly that is coupled to the aircraft. The air handling assembly includes at least one air inlet port. The apparatus also includes an air delivery assembly that is in air receiving communication with the air handling assembly. The air delivery assembly includes at least one nozzle that is configured to direct air into a first space adjacent a first side of the landing gear brake to create an air pressure differential across the landing gear brake. | 08-28-2014 |
20140374538 | AIRCRAFT LANDING GEAR - An aircraft landing gear having a strut having an upper portion for mechanically coupling to an aircraft and a lower portion movably mounted with respect to the upper portion. A bogie beam is pivotally coupled to the lower strut. A bogie control linkage is mechanically coupled to the bogie at a first connection point, and to the strut at a second connection point. The bogie control linkage has: an actuator including a locking system that inhibits actuation of the actuator; a sensor linkage mechanically coupled to the lower strut and arranged to change between first and second conditions in accordance with movement of the upper strut relative to the lower strut; and an actuator control linkage arranged to operate the locking system when the sensor linkage is in the first condition and arranged not to operate the locking system when the sensor linkage is in the second condition. | 12-25-2014 |
20150021434 | SELF-ORIENTING AIRCRAFT LANDING GEAR - An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage. | 01-22-2015 |
20150136902 | AIRCRAFT BRAKE ASSEMBLY - An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground. | 05-21-2015 |
20150314859 | AIRCRAFT UNDERCARRIAGE LEG INCLUDING A UNIT FOR DRIVING THE WHEELS - Aircraft undercarriage leg including an axle ( | 11-05-2015 |
20160009381 | SYSTEM FOR FAST FIXING AN ACCESSORY TO A DRONE BODY | 01-14-2016 |
20160009382 | SELF-ORIENTING AIRCRAFT LANDING GEAR | 01-14-2016 |
20160052624 | Method of Operating Aircraft Drive To Move an Aircraft Under Adverse Ground Conditions - A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed. | 02-25-2016 |
20160090173 | AIRCRAFT LANDING GEAR - An aircraft landing gear comprising an axle ( | 03-31-2016 |
20160096619 | AIRCRAFT UNDERCARRIAGE - An undercarriage comprising at least:
| 04-07-2016 |
20160101847 | NOSE WHEEL STEERING - A nose wheel steering mechanism comprises a first, rotationally fixed nose wheel leg portion and a second, rotatable nose wheel leg portion arranged at least partially within and extending parallel to the first nose wheel leg portion. A toroidal electric motor is mounted to and extends around the first nose wheel leg portion. Toroidal gearing is mounted to and extends around the first nose wheel leg and has an input driven by the toroidal electric motor and an output coupled to and driving the second nose wheel leg portion. | 04-14-2016 |
20160107747 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut. | 04-21-2016 |
20160144982 | UAV DOCKING SYSTEM AND METHOD - An aerial vehicle docking system includes a landing pad and an aerial vehicle. The landing pad has a concave landing surface and a depression. The aerial vehicle has landing gear and a protrusion. The protrusion is shaped to mate with the depression. The protrusion and the landing gear are positioned on a bottom surface of the aerial vehicle. | 05-26-2016 |
20160159469 | METHOD FOR USING AIRCRAFT WHEEL TYRE PRESSURE TO IMPROVE AIRCRAFT ENERGY EFFICIENCY AND DRIVE SYSTEM PERFORMANCE - A method for improving both drive system performance and energy efficiency performance both in an aircraft equipped with one or more drive wheel drive systems to move the aircraft autonomously on the ground is provided and in an aircraft that relies on its engines for ground movement. Achieving these objectives takes advantage of a discovered relationship between aircraft tyre pressure, drive system performance, and energy efficiency. Monitoring and maintaining tyre inflation pressure of an aircraft's tyres at an inflation level near a high end or recommended maximum cold or hot operating pressure for a specific kind of aircraft tyre on a specific aircraft not only improves drive wheel drive system performance, but also substantially and significantly improves energy efficiency in all types of aircraft. | 06-09-2016 |
20160167771 | DEVICE FOR MOUNTING AN AIRCRAFT TAIL WHEEL | 06-16-2016 |
20160169762 | COMBINATION TIRE PRESSURE SENSOR AND OVER-INFLATION PRESSURE RELIEF VALVE | 06-16-2016 |
20120305704 | CONTROL DEVICE FOR AIRCRAFT - The invention relates to a control device for aircraft comprising at least one aircraft undercarriage | 12-06-2012 |
20130112809 | Apparatus for Pre-Rotating Aircraft Tires - A disc-shaped accessory having radially-hinged flaps is adapted to be attached to an aircraft wheel. The flaps open no more than 90° (preferably 45-70°) in an airstream to exert a rotational torque on the wheel, causing the wheel to spin. The rotation helps reduce tire wear and damage during aircraft landing. | 05-09-2013 |
20140048648 | Free Spinning Wheel for Airplanes - The landing gear wheels of an aircraft include modified tires mounted on the rim of the wheel include a plurality of fins integral with the sidewall of the tires and configured to catch the wind created by movement of the aircraft through the air for spinning the wheel in a forward motion direction when the landing gear has been deployed and before the aircraft touches down, thereby reducing the friction between the runway and the tire upon touchdown. | 02-20-2014 |
20150021435 | Apparatus for causing an aircraft wheel to rotate - A rotator assembly for rotating an aircraft landing wheel by the action of the airstream flowing thereby has a circular plate mounted on the wheel and a plurality of independently movable cone shape connected to the outer surface of the plate in circumferentially spaced relation. Each cone shape member has a circle leading edge facing generally in the direction in which the wheel is to be rotated. As the wheel rotates, the members, which were previously pivoted outward, become engaged by the airstream and are sequentially forced inward against the plate. | 01-22-2015 |
20150314862 | WHEEL MOTORIZING SYSTEM, NOTABLY FOR AN AIRCRAFT WHEEL - Wheel motorization system, notably for an aircraft running along the ground, comprising an electric motor ( | 11-05-2015 |
20150329202 | CONTROL OF GROUND TRAVEL AND STEERING IN AN AIRCRAFT WITH POWERED MAIN GEAR DRIVE WHEELS - A controllable aircraft taxi system is provided that enables the simultaneous control of aircraft autonomous ground movement and direction of aircraft autonomous ground movement. Independently controlled non-engine drive means capable of driving an aircraft landing gear wheel to move an aircraft autonomously on the ground without reliance on the aircraft's main engines are mounted to provide driving torque to aircraft a selected number of main landing gear wheels. The aircraft nose landing gear steering system is provided with steering angle detection and measurement means adapted to communicate with main landing gear wheel non-engine drive means, enabling simultaneous control over both autonomous aircraft ground travel and direction of autonomous aircraft ground travel. The present invention overcomes steering challenges presented by using non-engine drive means on main landing gear wheels to drive aircraft autonomously during taxi. | 11-19-2015 |
20160039519 | LANDING GEAR DRIVE SYSTEM - The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion. | 02-11-2016 |
20160176516 | AIRCRAFT LANDING GEAR | 06-23-2016 |
20160194077 | SPACE-MAXIMIZING CLUTCH ARRANGEMENT FOR VEHICLE DRIVE WHEEL | 07-07-2016 |
20160200424 | TIRE SPINNING ASSEMBLY | 07-14-2016 |