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公开(公告)号：US20240190557A1
公开(公告)日：2024-06-13
申请号：US18233943
申请日：2023-08-15
Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH , AIRBUS HELICOPTERS
Inventor： Axel FINK , Reynaldo OIOLI-NETO , Didier BERTIN
Abstract: A non-retractable wheel-type landing gear for a rotorcraft, comprising: at least one wheel; a shock absorber with a circumferential direction, which is connected to the at least one wheel and comprises a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; a mounting arm extending laterally from the shock absorber tube, the mounting arm being integrally formed with the shock absorber tube and adapted for attachment to a first fitting of a rotorcraft; and a link fixation extending laterally from the shock absorber tube, the link fixation being arranged in the circumferential direction of the shock absorber at an angle in a range from 45° to 120° with respect to the mounting arm and adapted for connection to a second fitting of the rotorcraft.
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公开(公告)号：US20240182159A1
公开(公告)日：2024-06-06
申请号：US18133850
申请日：2023-04-12
Applicant: Hyundai Motor Company , Kia Corporation
Inventor： Choung Hyoung Kim , Jung Hyun Lee , Eugene Hwang
Abstract: A landing gear system may include: a casing coupled to a fuselage of an aircraft, such as an urban air mobility vehicle; a steering, one side of which is inserted into the casing and the other side of which is connected to a tire; a magnetorheological (MR) damper including a cylinder coupled to the casing and a piston coupled to the steering rod; a sensor unit configured to measure a condition of the urban air mobility vehicle; and a controller configured to control damping force of the MR damper based on measurement data of the sensor unit. The sensor unit may include a first sensor for measuring a stroke of the MR damper and a second sensor for measuring an acceleration of the casing.
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公开(公告)号：US11981424B2
公开(公告)日：2024-05-14
申请号：US17774925
申请日：2020-11-10
Applicant: Safran Landing Systems UK LTD , Safran Landing Systems
Inventor： Antoine Guidoux , Jon Smith , Jean-Yves Ravel , Yann Simmonneaux
CPC classification number: B64C25/60 , B64D45/00 , B64F5/60 , B64D2045/008 , B64D2045/0085
Abstract: A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.
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公开(公告)号：US20240140597A1
公开(公告)日：2024-05-02
申请号：US18049918
申请日：2022-10-26
Applicant: SAFRAN LANDING SYSTEMS CANADA INC.
Inventor： Zoran PASIC , Michael SACCOCCIA , Randy LEE
IPC: B64C25/60
CPC classification number: B64C25/60
Abstract: A main fitting includes an elongate piston and a cylinder configured to slidingly receive the piston. A first end of the piston extends from a first end of the cylinder, and a second end of the piston extends from a second end of the cylinder. The first end of the cylinder comprises a bearing surface engaging the piston to limit translation of the piston relative to the cylinder to a longitudinal direction.
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公开(公告)号：US11913823B2
公开(公告)日：2024-02-27
申请号：US17086344
申请日：2020-10-31
Applicant: C. Kirk Nance
Inventor： C. Kirk Nance
CPC classification number: G01G19/07 , B64C25/60 , F16F9/0209 , G01G19/028 , F16F2222/04 , F16F2230/0047 , F16F2230/08
Abstract: Aircraft landing gear strut breakout friction values are used to correct measured strut pressure as related to the amount of weight supported; with the ability to generate and refine the breakout friction value database, and ability to predict a future breakout friction correction value by trending historical measurements, as compared to recent measurements, as further compared to real-time breakout friction values. The system is used in monitoring, measuring, computing and displaying the weight and center of gravity for aircraft utilizing telescopic oleo landing gear struts. Pressure sensors, temperature sensors, humidity sensors, axle deflection sensors, accelerometers, inclinometers are mounted in relation to each of the landing gear struts to monitor, measure and record strut pressure as related to strut telescopic movement, rates of strut telescopic movement, axle deflection, current temperature, current relative humidity, vertical acceleration; experienced by landing gear struts, as the aircraft proceeds through typical ground and flight operations.
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Patent Agency Ranking
公开(公告)号：US11794884B1
公开(公告)日：2023-10-24
申请号：US16913195
申请日：2020-06-26
Applicant: SiFly Aviation, Inc.
Inventor： Brian L. Hinman , Jeffrey G. Bernstein
Abstract: An improved vertical takeoff aircraft of the type having a set of pads that are in contact with the ground when the aircraft is at rest on the ground and a controllable lift and propulsion system. The aircraft includes an array of force sensors coupled to the set of pads. The array has an output providing measurements over time of forces exerted on the pads along at least two independent axes. The aircraft also includes a controller, coupled to the lift and propulsion system and to the array of force sensors. The controller is configured to control the lift and propulsion system in a manner to counteract forces exerted externally on the aircraft that would cause undesired motion of the aircraft when on the ground and transitioning from the ground to flight.
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7.发明公开公开(公告)号：US20230331376A1
公开(公告)日：2023-10-19
申请号：US16542141
申请日：2019-08-15
Applicant: Meta Platforms, Inc.
Inventor： Oliver Ensslin
CPC classification number: B64C25/44 , B64C39/024 , B64C25/62 , B64C25/60 , B64C25/28 , B64C2201/021
Abstract: The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.
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公开(公告)号：US20230322410A1
公开(公告)日：2023-10-12
申请号：US18298907
申请日：2023-04-11
Applicant: Villya, LLC
Inventor： William Miller , Greg Swan
CPC classification number: B64F5/40 , B64F5/60 , B64C25/60 , F04B49/225 , F04B19/04 , F04B2205/05
Abstract: A servicing tool may provide a portable, lightweight solution to adjusting the height of struts of aircraft. The tool may provide hydraulic fluid at high pressure to an already pressurized strut. The hydraulic fluid may be supplied to the strut by the tool at a pressure in excess of a pressured gas in the strut to increase the height of the strut. The tool provides techniques to raise and lower the strut when access to high-pressure gas is unavailable. Further, with the application of high-pressure hydraulic fluid, the tool may be used to increase the strut height while also increasing the stiffness of the strut so as to reduce a risk of dynamic rollover.
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公开(公告)号：US20190071169A1
公开(公告)日：2019-03-07
申请号：US16104680
申请日：2018-08-17
Applicant: THE BOEING COMPANY
Inventor： Terrence S. BIRCHETTE , Akif O. BOLUKBASI
Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.
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公开(公告)号：US20180086441A1
公开(公告)日：2018-03-29
申请号：US15816353
申请日：2017-11-17
Applicant: SZ DJI TECHNOLOGY CO., LTD.
Inventor： Di OU
CPC classification number: B64C25/52 , B64C1/36 , B64C25/06 , B64C25/60 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64D2221/00 , H02G3/04 , H02G3/0406 , H02G3/0462
Abstract: A signal line protection assembly connecting to a propulsion system of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve including an electronic speed controller compartment arranged below a motor of the propulsion system and forming a closed space to receive an electronic speed controller of the aerial vehicle. The protection sleeve is configured to receive a power line for the electronic speed controller. At least a portion of the protection sleeve is received in the electronic speed controller compartment.
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