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公开(公告)号：US12084169B2
公开(公告)日：2024-09-10
申请号：US18049941
申请日：2022-10-26
发明人： Michael Saccoccia
摘要： A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.
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公开(公告)号：US12054241B2
公开(公告)日：2024-08-06
申请号：US18011939
申请日：2021-06-21
摘要： A locking device locks a landing gear mounted in rotation on an aircraft and includes a deployment hydraulic jack including a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device includes a hydraulic actuator connected to a rotary distributor. The rotary distributor includes a coupling operationally connecting the rotary distributor to a strut of the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.
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公开(公告)号：US20240132205A1
公开(公告)日：2024-04-25
申请号：US18224392
申请日：2023-07-19
申请人： M Nizar Sanadiki
发明人： M Nizar Sanadiki
CPC分类号： B64C25/26 , B64C25/20 , B64C25/405
摘要： An aircraft landing gear control system. As an aircraft prepares to land, the system determines the ground speed of the aircraft and causes the aircraft's wheels to rotate at an angular velocity that corresponds to the aircraft's ground speed so that upon landing, the aircraft wheels are not subjected to a sudden jarring impact.
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公开(公告)号：US20240127703A1
公开(公告)日：2024-04-18
申请号：US18062497
申请日：2022-12-06
CPC分类号： G08G5/065 , B60T3/00 , G01C21/20 , G08G5/0021 , B64C25/26
摘要： A method including: receiving data associated with a unique identity of a vehicle asset to identify the vehicle asset; receiving data associated with a unique identity of a smart wheel chock to identify the smart wheel chock; associating the identified vehicle asset with the identified smart wheel chock, such that a location of the smart wheel chock can represent a location of the vehicle asset; receiving location data associated with the location of the smart wheel chock, wherein the received location data is based, at least in part, on location data generated by one or more systems on the smart wheel chock; and identifying the vehicle asset location based on the received smart wheel chock location data such that the vehicle asset can be determined and relayed to a user device to locate the vehicle asset.
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公开(公告)号：US11801932B2
公开(公告)日：2023-10-31
申请号：US16730108
申请日：2019-12-30
申请人： JETZERO, INC.
发明人： Ewald Schuster , Jennifer Whitlock , Joshua B Long , Cristina Donastorg , Brendan Kennelly , Mark A. Page
CPC分类号： B64C25/22 , B64C25/001 , B64C25/04 , B64C25/26 , B64C25/40 , B64F5/60 , B64C2025/008
摘要： Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.
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公开(公告)号：US20230322370A1
公开(公告)日：2023-10-12
申请号：US17714857
申请日：2022-04-06
申请人： GOODRICH CORPORATION
发明人： HARALD KLODE , KYLE M. MADEY , GERARD COX
摘要： A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.
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公开(公告)号：US11753148B2
公开(公告)日：2023-09-12
申请号：US17354787
申请日：2021-06-22
发明人： Ladislao López López
摘要： A landing gear door system, including a landing gear bay including an opening and accommodating a landing gear in a retracted position, a landing gear door for opening and closing the opening, an actuator for operating the landing gear door between an open and a closed position, a lock located in the landing gear bay and latching the landing gear door in the closed position, a stop fitting located in the landing gear bay and configured to be in connection with the landing gear door at least in its latched position. The landing gear door system further includes an additional actuator configured to apply a force to the landing gear door in its closed position and to elastically deform the landing gear door towards the landing gear door bay.
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公开(公告)号：US11713110B2
公开(公告)日：2023-08-01
申请号：US17502505
申请日：2021-10-15
发明人： Blaine Knight Rawdon
CPC分类号： B64C25/26 , B64C25/001 , F15B1/02 , F15B15/18 , B64C2025/008 , B64C2039/105 , F15B2211/30
摘要： Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.
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公开(公告)号：US11691717B2
公开(公告)日：2023-07-04
申请号：US17506300
申请日：2021-10-20
发明人： Daniel Bellet , Alexandre Legardez
摘要： A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.
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公开(公告)号：US20190241256A1
公开(公告)日：2019-08-08
申请号：US16265041
申请日：2019-02-01
发明人： Daniel Moine , Hervé Rolinat
摘要： An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.
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