公开(公告)号：WO2022171007A1

公开(公告)日：2022-08-18

申请号：PCT/CN2022/074631

申请日：2022-01-28

Applicant: 汉王科技股份有限公司

Inventor： 王彦伟

IPC: B64C1/00 ,  A63H27/00

Abstract: 一种飞行器、飞行器的机套和用于更换飞行器的机套的方法，该飞行器（100）包括：机头（110），设置在飞行器的前端，用于指向飞行器的飞行方向；机身（120），与机头连接，用于安装机翼和尾翼；机套（130），用于包覆机头和/或机身；其中，机套包括机头套（132）和/或机身套（134）；机头套设置有第一开口（132_2），通过该第一开口将机头套套装于机头，使得机头套包覆机头；机身套设置有第二开口（134_2），通过该第二开口将机身套套装于机身，使得机身套包覆机身。

公开(公告)号：WO2022003464A1

公开(公告)日：2022-01-06

申请号：PCT/IB2021/055231

申请日：2021-06-14

Applicant: HELENG INC.

Inventor： JENG, Jack Ing

IPC: B64C39/02 ,  B64D41/00 ,  B64C1/36 ,  B64C1/00 ,  B64C1/068 ,  B64C1/16 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/108 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/08 ,  B64D2027/026 ,  B64D27/10 ,  B64D27/24 ,  F02C7/00 ,  F02C7/264 ,  F02K1/002 ,  F05D2220/323 ,  F23R3/26 ,  H04B7/0413

Abstract: A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

公开(公告)号：WO2021224207A1

公开(公告)日：2021-11-11

申请号：PCT/EP2021/061623

申请日：2021-05-04

Applicant: PREMIUM AEROTEC GMBH

Inventor： RENNECKE, Chris ,  GENSEWICH, Christian

IPC: B29C70/30 ,  B29C70/34 ,  B29C70/44 ,  B29C70/54 ,  B64C1/06 ,  B64C3/18 ,  B29C53/04 ,  B29D99/00 ,  B29B11/16 ,  B29C70/38 ,  B64C1/00

Abstract: Die Erfindung schafft ein Verfahren zur Herstellung eines bogenartig ausgebildeten Faserverbundbauteils. Es wird eine Preform mit einer entlang eines Bogens gebildeten flächigen Faserschichtenanordnung, die einen einer konvexen Außenseite des Bogens zugeordneten Außenrand aufweist, ausgebildet. Der Außenrand wird in der Weise mit sich in die flächige Faserschichtenanordnung hinein erstreckenden Ausnehmungen ausgebildet, dass eine Kontur der Ausnehmungen jeweils zumindest abschnittsweise nahe einer Zielkontur einer in dem Faserverbundbauteil jeweils vorzusehenden Aussparung ausgebildet wird. Die Preform wird in der Weise umgeformt, dass zumindest ein erster Bereich der flächigen Faserschichtenanordnung, der sich an den Außenrand anschließend im Wesentlichen in Richtung des Bogens erstreckt, relativ zu einem von der Außenseite des Bogens abgewandt an den ersten Bereich anschließenden zweiten Bereich der flächigen Faserschichtenanordnung abgebogen oder abgewinkelt wird. Bei der Bildung der umgeformten Preform gehen die Ausnehmungen, die die Preform vor dem Umformen aufweist, in Ausnehmungen der umgeformten Preform über und bleiben geöffnet. Vorgeschlagen wird ferner eine Preform für die Herstellung eines bogenartig ausgebildeten Faserverbundbauteils mittels eines derartigens Verfahrens. Die Erfindung kann insbesondere dazu beitragen, bei der Herstellung des Faserverbundbauteils Material und Arbeitsschritte einzusparen sowie Verschnitt zu vermeiden.

公开(公告)号：WO2021206820A1

公开(公告)日：2021-10-14

申请号：PCT/US2021/019222

申请日：2021-02-23

Applicant: AERION INTELLECTUAL PROPERTY MANAGEMENT CORPORATION

Inventor： BARNES, Edward

IPC: B64C1/00 ,  B64C1/12 ,  B64C1/18

Abstract: Improved methods and devices for shielding electrical and electronic aircraft components and their associated cables and wires from cross-coupling and electrical and magnetic interference and dissipating excess heat from the electrical and electronic aircraft components and cables and wires. An aircraft structure formed primarily of composite materials includes an outer wall; an inner wall; and a plurality of spaced-apart dividers extending transversely from and integrally formed with the inner wall. The dividers define a series of spaced-apart channels that are each partially enclosed by adjacent pairs of the dividers. A layer of electrically conductive foil covers the dividers and the channels to create a current return network in the channels. Wires and cables may be placed in the channels between adjacent pairs of the dividers to reduce cross-coupling between the wires and cables and shield the wires and cables from electromagnetic fields.

公开(公告)号：WO2021198964A1

公开(公告)日：2021-10-07

申请号：PCT/IB2021/052712

申请日：2021-03-31

Applicant: ALDARWISH, Ahmad Fareed

Inventor： KAYYANI, Saeed

IPC: B64C21/02 ,  B64C1/00 ,  B64C3/36 ,  B64F5/00 ,  B64C23/06

Abstract: An aircraft including a fuselage with one or more wings extending from the fuselage. The aircraft may include one or more apertures in a surface of at least one of the fuselage and the one or more wings. The one or more apertures may be configured to enable air to pass through the one or more apertures when the aircraft is flying.

公开(公告)号：WO2021161717A1

公开(公告)日：2021-08-19

申请号：PCT/JP2021/001299

申请日：2021-01-15

Applicant: 三菱重工業株式会社

Inventor： 宇野　徳馬 ,  滝沢　智生 ,  山口　弘晃 ,  岡田　篤志 ,  吉野　駿佑 ,  村木　俊宣

IPC: B32B5/28 ,  B64D45/02 ,  B64C1/00 ,  B64C1/06 ,  B32B7/12

Abstract: 複合材料構造体において、導電性を有する第１強化繊維に第１樹脂が含浸された複数の第１複合材料シートが積層される第１複合材料と、導電性を有する第２強化繊維に第２樹脂が含浸された第２複合材料と、第１複合材料と第２複合材料との間に配置されて第１複合材料と第２複合材料とを接着する絶縁性接着層と、複数の第１複合材料シートを接続する導電性部材とを備える。

公开(公告)号：WO2021148775A1

公开(公告)日：2021-07-29

申请号：PCT/GB2021/050053

申请日：2021-01-08

Applicant: BAE SYSTEMS PLC

Inventor： THOMPSON, Gregory Warren

IPC: B64C1/06 ,  B64C39/00 ,  B64C1/00 ,  B64C1/061 ,  B64C1/068 ,  B64C2001/0045 ,  B64C2201/00

Abstract: An airframe 1 or part thereof comprises a set of modular cells 10, including a first cell 10A comprising a set of profiles 100 including: a first structural profile 100A, having a first length L1 and enclosing a first volume V1 providing a first passageway P1; and a second profile 100B, having a second length L2 and enclosing a second volume V2, wherein the first passageway P1 is arranged to receive the second profile 100B therein.

公开(公告)号：WO2021148335A1

公开(公告)日：2021-07-29

申请号：PCT/EP2021/050885

申请日：2021-01-18

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： THOMPSON, Robert

IPC: B64D37/04 ,  B64D37/30 ,  B64C1/00 ,  B64C2001/0036 ,  B64C2001/0045

Abstract: An aircraft fuselage comprising a fuselage shell; and a fuel tank outside the fuselage shell, wherein the fuselage shell has a double-lobed cross section and at least part of the fuel tank is located in a channel between the two lobes.

公开(公告)号：WO2021112961A2

公开(公告)日：2021-06-10

申请号：PCT/US2020/056456

申请日：2020-10-20

Applicant: HEXCEL CORPORATION

Inventor： ZHU, Yan ,  EMMERSON, Gordon T.

IPC: C08J5/24 ,  B64C1/00 ,  B64C2001/0072 ,  B64C2027/4736 ,  C08J2363/00 ,  C08J2363/04 ,  C08J2363/06 ,  C08J2477/02 ,  C08J2477/06 ,  C08J2481/06 ,  C08J5/249 ,  C08K2003/265 ,  C08K3/013 ,  C08K3/046 ,  C08K5/0025 ,  C08K5/375 ,  C08K5/41

Abstract: Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts. The prepreg includes carbon reinforcing fibers and an uncured resin matrix. The resin matrix includes an epoxy resin component, polyethersulfone as a toughening agent, a thermoplastic particle component, a nanoparticle component and a curing agent

公开(公告)号：WO2021046558A1

公开(公告)日：2021-03-11

申请号：PCT/US2020/049785

申请日：2020-09-08

Applicant: ZSM HOLDINGS LLC

Inventor： KARNI, Etan, D. ,  LUNDSTROM, Mark, Emil

IPC: B64C1/00 ,  B64C1/14 ,  B64C1/22 ,  B64C39/00 ,  B64C39/02 ,  B64D9/00 ,  B64D13/00 ,  B64F1/32 ,  B65G67/00

Abstract: A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.