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    ROTORCRAFT WITH A NON-RETRACTABLE WHEEL-TYPE LANDING GEAR
    1.
    发明公开
    ROTORCRAFT WITH A NON-RETRACTABLE WHEEL-TYPE LANDING GEAR 审中-公开

    公开(公告)号：US20240294251A1

    公开(公告)日：2024-09-05

    申请号：US18509696

    申请日：2023-11-15

    申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

    发明人： Axel FINK ,  Reynaldo OIOLI-NETO

    IPC分类号： B64C25/36 ,  B64C25/06 ,  B64C25/32 ,  B64C25/58

    CPC分类号： B64C25/36 ,  B64C25/06 ,  B64C25/58 ,  B64C2025/325

    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.

    Vertical takeoff and landing UAV
    2.
    发明授权
    Vertical takeoff and landing UAV 有权

    公开(公告)号：US11608172B2

    公开(公告)日：2023-03-21

    申请号：US17827490

    申请日：2022-05-27

    申请人： Shanghai Autoflight Co., Ltd.

    发明人： Yu Tian

    IPC分类号： B64C39/02 ,  B64C25/06 ,  B64C29/00

    摘要： A vertical takeoff and landing (VTOL) UAV having a UAV main body, two rear landing gears and two front landing gears; the two rear landing gears are fixedly connected to both sides of the rear bottom of the UAV main body, respectively; the two front landing gears are rotatably connected to both sides of the front bottom of the UAV main body, respectively. One end of the front landing gear away from the UAV main body is provided with a locating block. Rotating the front landing gear enables the locating block mounted on the front landing gear to get close to or away from the UAV main body.

    RHOMBOHEDRAL-WING AIRCRAFT FOR VERTICAL TAKE-OFF AND/OR LANDING
    4.
    发明申请
    RHOMBOHEDRAL-WING AIRCRAFT FOR VERTICAL TAKE-OFF AND/OR LANDING 审中-公开

    公开(公告)号：US20200156780A1

    公开(公告)日：2020-05-21

    申请号：US16605001

    申请日：2018-04-09

    申请人： FLY-R

    发明人： François VARIGAS

    IPC分类号： B64C29/00 ,  B64C3/10 ,  B64C25/04 ,  B64C25/06 ,  B64C39/06 ,  B64C27/28

    摘要： The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18).At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27).The rear end of the fuselage supports an engine (21) provided with a propeller (22).The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

    Wheel-Strut Stabilization System for Suspended Payload Aircraft
    7.
    发明申请
    Wheel-Strut Stabilization System for Suspended Payload Aircraft 审中-公开

    公开(公告)号：US20190185144A1

    公开(公告)日：2019-06-20

    申请号：US15762671

    申请日：2016-09-08

    申请人： Thomas MCNALLY

    发明人： Thomas MCNALLY

    IPC分类号： B64C25/04 ,  B64C25/06 ,  B64C39/02 ,  B64D9/00

    CPC分类号： B64C25/04 ,  B64C25/06 ,  B64C39/02 ,  B64D9/00 ,  B64D9/003 ,  Y02T50/46

    摘要： A payload transport aircraft that includes a nacelle including a cockpit, a first wing extending in a first direction from the nacelle and a second wing extending in a second direction from an opposing side of the nacelle. The aircraft also includes a first pair of wheel-struts extending between the first wing and a first set of corresponding wheels and a second pair of wheel-struts extending between the second wing and a second set of corresponding wheels. Each member in the pair of wheel-struts is connected by a wheel-strut stabilizing segmented cross-bar having a rear segment and a front segment joined at a disconnection point by one or more coil-springs, which can be tension springs resistant to stretching mounted to each segment through the use of spring mounting-posts fitted into each segment and protected using a cover that can be removable and transparent for quick visual inspection.

    SUSPENSION FOR LANDING CONDITION
    10.
    发明申请
    SUSPENSION FOR LANDING CONDITION 审中-公开

    公开(公告)号：US20180257764A1

    公开(公告)日：2018-09-13

    申请号：US15453527

    申请日：2017-03-08

    申请人： Toyota Motor Engineering & Manufacturing North America, Inc.

    发明人： Umesh N. Gandhi ,  Matthew C. Clontz

    IPC分类号： B64C25/58 ,  B64C25/34 ,  B64C25/06 ,  B60F5/02 ,  F16F7/10

    摘要： An aerocar with a dual mode suspension system configured to operate in a roadable mode and a flight mode. The aerocar may include a front suspension assembly having a front axle, and a rear suspension assembly having a rear axle. A conduit system provides a hydraulic fluid in fluid communication between the front suspension assembly and the rear suspension assembly. An auxiliary hydraulic fluid reservoir is provided in fluid communication with the conduit system, and configured to selectively maintain or interrupt fluid communication between the front suspension assembly and the rear suspension assembly to adjust damping of the front suspension assembly. A controller may be provided, configured to direct the flow of hydraulic fluid from the rear suspension assembly to the front suspension assembly, for example, when a stroke of the rear suspension exceeds a predetermined value during landing.