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公开(公告)号：US20230133313A1
公开(公告)日：2023-05-04
申请号：US17978904
申请日：2022-11-01
摘要： A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.
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公开(公告)号：US11639093B2
公开(公告)日：2023-05-02
申请号：US17115271
申请日：2020-12-08
摘要： A transaxle system for a golf car, wherein the system comprises a transaxle and a mating interface. The transaxle comprises a plurality of mounting flanges fixedly mountable to at least one axle tube of the golf car, wherein the at least one axle tube houses at least one wheel axle, and the transaxle is operably couplable to the at least one wheel axle. The transaxle additionally comprising a transaxle mounting collar that is fixedly mounted to or integrally formed with a housing of the transaxle. The mating interface is mountable to the transaxle mounting collar, and is structured and operable to have an integrated internal combustion engine-transmission unit of the golf car mounted thereto.
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3.发明授权公开(公告)号：US11628601B2
公开(公告)日：2023-04-18
申请号：US17378232
申请日：2021-07-16
发明人： David G. Carlson
摘要： One embodiment is an apparatus including a mold configured to manufacture a composite structure at a heated temperature. The mold includes a first mold tool configured to mold a first portion of the composite structure, wherein the first mold tool comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands; and an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the first mold tool; and a second mold tool configured to mold a second portion of the composite structure.
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公开(公告)号：US11623736B2
公开(公告)日：2023-04-11
申请号：US17336264
申请日：2021-06-01
IPC分类号： B64C13/04
摘要： An aircraft includes an electronically controlled engine (ECE) and a first and a second throttle control assembly. The first throttle control assembly includes a first throttle fly button configured to command a FLY mode and a first throttle idle button configured to command an IDLE mode. The second throttle control assembly includes a second throttle fly button configured to command the FLY mode and a second throttle idle button configured to command the IDLE mode.
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公开(公告)号：US11619295B2
公开(公告)日：2023-04-04
申请号：US17512974
申请日：2021-10-28
发明人： Scott David Poster
摘要： A bypass apparatus for lubricant in an unregulated pressurized gearbox including: a block including a lubricant inlet in fluid communication with a pressure relief valve, wherein the pressure relief valve diverts lubricant into the gearbox or into an oil filter, wherein lubricant is returned to the gearbox when the lubricant is cold and/or pressure at the pressure relief valve is high to reduce damage to the gearbox caused by high pressure during a cold start, and when the lubricant temperature increases and the pressure is reduced the pressure relief valve closes and lubricant enters the oil filter.
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公开(公告)号：US20230078659A1
公开(公告)日：2023-03-16
申请号：US17472907
申请日：2021-09-13
IPC分类号： B60L58/26 , B64C29/00 , B64D13/00 , H01M10/625 , H01M10/6567
摘要： A battery system includes a plurality of battery modules each formed from a plurality of battery cells. A shared cooling structure is thermally coupled to each of the battery modules. The shared cooling structure is configured to conduct heat relative to the battery modules. A thermal interface is disposed between the battery cells of each battery module and the shared cooling structure. Each thermal interface is configured to transition from a first thermal conductivity state to a second thermal conductivity state when heat generated by the respective battery cells exceeds a threshold level. The second thermal conductivity state is lower than the first thermal conductivity state such that after one of the thermal interfaces has transitioned from the first thermal conductivity state to the second thermal conductivity state, heat transfer from the respective battery cells to the shared cooling structure is reduced.
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公开(公告)号：US11603186B2
公开(公告)日：2023-03-14
申请号：US16248197
申请日：2019-01-15
发明人： William B. Wood , Lawrence M. Corso
摘要： A removable passive airflow oscillation device can be disposed within a pressurized wing structure utilized as a plenum. The passive airflow oscillation device can be a removable insert disposed into exterior vehicle surfaces with pressurization of a sealed chamber to provide the airflow. The device can include a cavity configured to receive the airflow from an ingress opening, direct the airflow therethrough to generate a predetermined oscillating airflow, and expel the oscillatory airflow from the egress opening. The removable passive airflow oscillation devices can provide quick and simple replacement and maintenance of damaged or clogged devices. The aft chamber of the flap seal can be sealed and pressurized to serve as a plenum providing the airflow to the actuators. The device can receive airflow, such as compressor air, and expel an oscillating airflow. Because each device is self-contained the number of devices and location thereof can vary by application.
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公开(公告)号：US11603183B2
公开(公告)日：2023-03-14
申请号：US17714967
申请日：2022-04-06
摘要： A compliant tail structure for a rotorcraft having rotating components and a fuselage. The tail structure includes a tail assembly having first and second oppositely disposed tail members. A tail joint connects the tail assembly to an aft portion of the fuselage. The tail joint includes at least four tail mounts configured to establish a nodding axis for the tail assembly. At least two of the tail mounts are resilient tail mounts that are configured to establish a nodding degree of freedom for the tail assembly relative to the fuselage about the nodding axis, thereby detuning dynamic fuselage responses from excitation frequencies generated by the rotating components.
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公开(公告)号：US11597510B2
公开(公告)日：2023-03-07
申请号：US16833622
申请日：2020-03-29
IPC分类号： B64C29/00 , B64C11/00 , B64C21/04 , B64D27/16 , B64C11/48 , B64D35/06 , B64D35/02 , B64C27/22 , B64D33/04 , B64D35/04 , B64C3/10 , B64C19/00 , B64C27/26 , B64C27/30 , B64C9/20 , B64C21/08 , B64C27/78 , B64C39/10 , B64C9/18 , B64C15/02 , B64C15/14 , B64C21/00
摘要： A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.
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公开(公告)号：US11587456B2
公开(公告)日：2023-02-21
申请号：US17354999
申请日：2021-06-22
摘要： Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.
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