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139 条记录 (耗时 0.032 秒)

    Convertible Aircraft System
    1.
    发明申请
    Convertible Aircraft System 有权

    公开(公告)号：US20220315215A1

    公开(公告)日：2022-10-06

    申请号：US17220137

    申请日：2021-04-01

    申请人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

    发明人： Xingkang Li ,  Heng Ren ,  Qiang Li ,  Xingjian Li

    IPC分类号： B64C37/00 ,  B64C1/06 ,  B64C27/68 ,  B64D31/00 ,  B64C9/00 ,  B64D27/10 ,  B64C5/00

    摘要： A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

    AEROFOIL
    3.
    发明申请
    AEROFOIL 有权

    公开(公告)号：US20210039767A1

    公开(公告)日：2021-02-11

    申请号：US16983324

    申请日：2020-08-03

    申请人： ROLLS-ROYCE plc

    发明人： Chaitanya PARUCHURI ,  Philip JOSEPH

    IPC分类号： B64C3/14 ,  B64C5/00 ,  F01D9/04

    摘要： An aerofoil has a leading edge, a trailing edge, a suction surface and a pressure surface. The leading edge includes apertures extending through the aerofoil from the suction surface to the pressure surface. The apertures define a first row spaced a distance (L1) of between 2 and 6 cm from the leading edge in a chordal direction (C).

    NO-BACK DEVICE WITH ENERGY-DISPERSING SPRINGS
    4.
    发明申请
    NO-BACK DEVICE WITH ENERGY-DISPERSING SPRINGS 审中-公开

    公开(公告)号：US20170299001A1

    公开(公告)日：2017-10-19

    申请号：US15480856

    申请日：2017-04-06

    申请人： HS Wroclaw Sp. z o.o.

    发明人： Daniel Trybula

    IPC分类号： F16D59/02 ,  B64C5/00 ,  F16D125/32 ,  F16D121/14 ,  F16D127/00 ,  F16D125/58

    CPC分类号： F16D59/02 ,  B64C5/00 ,  F16D43/02 ,  F16D2121/14 ,  F16D2125/32 ,  F16D2125/582 ,  F16D2127/004

    摘要： A no-back device for resisting feedback torque from an actuator. The no-back device comprises: a flange arranged to receive torque via a shaft; a ratchet assembly comprising a ratchet wheel arranged parallel to the flange; and a braking assembly comprising a resistance wheel, which is sandwiched between the flange and the ratchet wheel, and a braking device, which acts on the resistance wheel to generate a resistive angular force reacting against torque exerted on the resistance wheel. The braking device comprises a follower arranged to roll, under bias from a spring in the braking device, on a cam surface extending around a circumferential perimeter of the resistance wheel. Radial displacement of the follower energizes the spring to generate resistive angular force.

    Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies
    6.
    发明授权
    Upper joints between outboard wing boxes and wing center sections of aircraft wing assemblies 有权
    飞机机翼组件外侧机翼和机翼中心部分之间的上部接头

    公开(公告)号：US09475570B2

    公开(公告)日：2016-10-25

    申请号：US13975158

    申请日：2013-08-23

    申请人： The Boeing Company

    发明人： Jordan Daniel Charles ,  Jason Hamada

    IPC分类号： B64C1/00 ,  B64C3/00 ,  B64C5/00 ,  B64C3/18 ,  B64C1/26

    CPC分类号： B64C1/26 ,  B64C3/00 ,  B64C3/182 ,  B64C3/187 ,  B64C2001/0072 ,  B64C2001/0081

    摘要： An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer.

    摘要翻译： 飞行器的机翼组件的上接头包括外侧上翼板，中心上翼板，肋和可操作地连接外侧上翼板，中心上翼板和肋的上接头组件。 在一些实施例中，外侧上部桁条可以被配置为不同于中心上部桁条。 在一些实施例中，中心上部纵梁的子集可以不直接与外侧上部纵梁相对。 在其他实施例中，对于上关节的至少大体上/后跨距，每个中心上纵梁可以直接与外侧上纵梁相对。

    FUSELAGE AND METHOD FOR REDUCING DRAG
    9.
    发明申请
    FUSELAGE AND METHOD FOR REDUCING DRAG 审中-公开
    用于减少DRAG的熔融和方法

    公开(公告)号：US20130062460A1

    公开(公告)日：2013-03-14

    申请号：US13605920

    申请日：2012-09-06

    申请人： Gennady Trofimovich KRESHCHISHINA ,  Larisa Trofimovna KRESHCHISHINA

    发明人： Gennady Trofimovich KRESHCHISHINA ,  Larisa Trofimovna KRESHCHISHINA

    IPC分类号： B64C1/38 ,  B64C1/26 ,  B64C1/14 ,  B64C5/00 ,  B64C5/02 ,  B64D27/14 ,  B64C23/00

    CPC分类号： B64C1/0009 ,  B64C1/14 ,  B64C1/26 ,  B64C5/02 ,  B64C21/00 ,  B64D27/14 ,  Y02T50/12 ,  Y02T50/166

    摘要： Aircraft engineering applicable for improving aerodynamic quality of helicopters, airplanes, including big airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, by reducing contact area between the external fuselage tail section surface and a high-speed air flow, area of contact is reduced by increasing surface area of holes in the fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is convex upwards, for example, curved upwards according to the shape of the airfoil convex side. The upper hole for the aerodynamic channel in the fuselage skin may be located along the fin middle portion divided lengthwise by the fin to right and left, in two. The aerodynamic channel is made through and may be open. The upper front edge aligned hole of the aerodynamic channel has a greater surface area than the rear hole aligned with the fuselage end.

    摘要翻译： 飞机工程适用于通过减少外部机身尾部截面与高速气流之间的接触面积，改善直升机，飞机，包括大型空中客车和两栖飞机，空气动力地面效应和气垫车辆的空气动力学质量， 通过增加机身尾部的孔的表面积来减少接触。 为了在不增加耐压性的情况下增加提升力，空气动力通道底部向上凸起，例如，根据翼型凸侧的形状向上弯曲。 机身皮肤空气动力学通道的上部孔可以沿翅片中间部分沿翅片左右方向分成两部分。 空气动力学通道通过并且可以是开放的。 空气动力学通道的上前缘对齐孔具有比与机身端对准的后孔更大的表面积。