ROTORCRAFT WITH A NON-RETRACTABLE WHEEL-TYPE LANDING GEAR

    公开(公告)号:US20240294251A1

    公开(公告)日:2024-09-05

    申请号:US18509696

    申请日:2023-11-15

    摘要: A rotorcraft comprising a fuselage forming at least one lower lateral fuselage compartment with at least a first fitting, a second fitting, and a third fitting; and at least one non-retractable wheel-type landing gear that comprises: at least one wheel; a shock absorber with a shock absorber tube having an open end and an axially opposed closed end, and a shock absorber rod telescopically mounted to the shock absorber tube via the open end; a first fixation provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation provided close to the closed end on the shock absorber tube and connected to the third fitting.

    Ground Support Equipment For A High Altitude Long Endurance Aircraft

    公开(公告)号:US20240228061A1

    公开(公告)日:2024-07-11

    申请号:US18236169

    申请日:2023-08-21

    发明人: Tom Millspaugh

    摘要: Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

    Clutch Actuator Assembly
    9.
    发明公开

    公开(公告)号:US20240043113A1

    公开(公告)日:2024-02-08

    申请号:US18365310

    申请日:2023-08-04

    IPC分类号: B64C25/32 F16D27/14

    CPC分类号: B64C25/405 F16D27/14

    摘要: A powered clutch actuator assembly for integration with a clutch assembly is provided. The actuator and clutch assemblies, sized to fit within constraints of an aircraft landing gear wheel-mounted taxi drive system, are engineered to occupy a default neutral disengaged position that prevents torque transfer when torque to move the aircraft should not be transferred to the taxi drive system. Multiple solenoids and diodes power rotational motion of the actuator assembly to move a bi-directional clutch component in a desired rotational direction during torque transfer. A locking solenoid automatically locks and maintains the actuator assembly in a neutral disengaged condition when none of the solenoids are powered and disengages the actuator assembly when one solenoid is powered to cause rotation of the actuator assembly. Solenoid supports structured to operate as integral heat sinks may direct heat to an on-aircraft heat sink, prolonging the working life of the actuator assembly.