| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Aircraft comprising an aircraft fuselage section and one of the same section | JP2009544436 | 2008-01-03 | JP5308354B2 | 2013-10-09 | ギャラント、ギヨーム; アグエラ、ダミエン; ベルナデット、フィリップ |
| The section has openings for receiving windows (11), and frames (10) each comprising an elliptical frame sector surrounding the corresponding opening. The sector has two branches (15, 16) arranged lateral to the opening, and comprising ends that are coupled so as to form Y at each of ends (17, 18) of the sector. The frame sector is made of resin or carbon fiber based composite material, and the branches form a housing to receive a maintaining clip (23) for fixing the corresponding window on the opening. | ||||||
| 82 | Landing gear storage compartment that size has become smaller | JP2010511692 | 2008-05-28 | JP5166523B2 | 2013-03-21 | グーリン，ベルナール; マルク，ローラン サン |
| 83 | Composite material structure, and aircraft main wing and fuselage provided therewith | JP2011023154 | 2011-02-04 | JP2012162147A | 2012-08-30 | TANAKA YUYA; SUZUKI HIDEYUKI; KANAYAMA YUTAKA; SATO KAZUTAKA; HATANO MASATAKE; SAITO AKIRA; WATANABE KOEI; ABE RYO |
| PROBLEM TO BE SOLVED: To provide a composite material structure that reinforces areas around holes against stress concentrations and also enables weight reduction.SOLUTION: A wing 1 has a box structure. A lower outer plate 3 on the wing 1 is provided with: a center section 3b, made of metal, which extends in one direction and in which access holes 5 are formed; and a front section 3a and a rear section 3c, both made of fiber reinforced plastic, which extend in the one direction and are connected to both sides of the center section 3b respectively. The metal used for the center section 3b is preferably a titanium alloy or an aluminum alloy. | ||||||
| 84 | Block member for opening | JP2010112782 | 2010-05-17 | JP2011240754A | 2011-12-01 | TACHIBANA KAZUKI |
| PROBLEM TO BE SOLVED: To provide a block member for an opening, which more reliably maintains a lightning protection function.SOLUTION: A first insulator 63 and a second insulator 65 are provided between a door body 30 and a wing inner surface 11b around an opening 12. If the first insulator 63 drops out, the second insulator 65 gets sandwiched between an inner peripheral flat portion 64 and the wing inner surface 11b. In the state that the first insulator 63 gets tightly sandwiched between an outer peripheral flat portion 62 and the wing inner surface 11b, the second insulator 65 faces to the wing inner surface 11b with a specified clearance C therebetween. In addition, the outer peripheral flat portion 62 is formed at a position more separated from the wing inner surface 11b than the leading edge surface 65a of the second insulator 65 attached to the inner peripheral flat portion 64. | ||||||
| 85 | Sealing device, the sealing device for a seal, and aircraft with a door that has been sealed to the conductor by the sealing device | JP2000348580 | 2000-11-15 | JP4618696B2 | 2011-01-26 | ニック・アンドリュー・パナイーデス; リチャード・レズリー・カーター |
| 86 | Aircraft comprising an aircraft fuselage section and one of the same section | JP2009544436 | 2008-01-03 | JP2010514628A | 2010-05-06 | アグエラ、ダミエン; ギャラント、ギヨーム; ベルナデット、フィリップ |
| 本発明は、フレームと、キャビンの窓（１１）を収容する開口とを備える、航空機の胴体セクションに関する。 本発明によれば、少なくともいくつかのフレームが、少なくとも１つの開口を囲繞する少なくとも１つのフレームセグメントを備え、前記フレームセグメントが、開口の側方に配置された２つの分枝（１５、１６）を備える。 分枝の両端は、フレームセグメントの両端（１７、１８）のそれぞれに、Ｙ字形を形成するように取り付けられている。
【選択図】図３ |
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| 87 | System with a water diverting device and a complex water diverting device | JP2008531625 | 2006-09-25 | JP2009509824A | 2009-03-12 | カルステン パウル |
| 【課題】航空機の搭乗者は、頭上に水滴が落ちない状態で航空機から出たいという要望がある。
【解決手段】水方向転換装置は、密封機構の側面部（８）に水方向転換部（２）および取付けのための取付部（３）を備え、接続部（４）を介して互いに連結される水方向転換部および取付部が存在し、力が水方向転換部に作用する場合に、弾性力をもって変形可能であり、取付部に関して移動可能である。 水方向転換装置は、ドアエリアで使用され、ドアが閉じられて密封機構の側面部とドア外板との間の空洞で停止する場合に変形し、一方、ドアが開けられる場合に再びその始動形状を呈する。 【選択図】図１ |
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| 88 | Contact for the hatch and aircraft having such a hatch | JP2008516363 | 2006-06-06 | JP2008546578A | 2008-12-25 | グロ，ベルナール; ゲラン，ベルナール; ベルジュレ，クリスティアン |
| 【課題】航空機のコックピット内のような狭く込み入った空間において、連絡用ハッチの扉の開け閉めの際に、各ドアパネルのストロークが邪魔されない構造を得る。
【解決手段】本発明は、壁体（Ｐ）上の開口部（６）に対するアクセスを塞ぐか、または、あけることを目的とし少なくとも二枚のドアパネル（３、４）を有する扉（２）を含む連絡用ハッチ（１）において、第一のドアパネル（３）が扉を開閉できるように壁上に軸支回動する状態で取付けられており、第二のドアパネル（４）が前記第一のドアパネルを中心としたストロークを有するように第一のドアパネル上に軸支回動する状態で取付けられていることを特徴とする連絡用ハッチに関する。 本発明は、また、かかるハッチ（１）を少なくとも一つ備えた航空機にも関する。 【選択図】図1Ｃ |
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| 89 | 향상된 댐핑 특성을 갖는 적층 구조물 | KR20187006027 | 2016-07-27 | KR20180037014A | 2018-04-10 | |
| 향상된소음-댐핑특성및 기계적특성을갖는적층구조물은여기에기재된다. 적층물은제1 유리기판과제2 유리기판사이에배치된중간층구조물로구성되며, 여기서상기중간층은, 적층물에의한소음감쇠또는댐핑이최적화되도록설계된고분자층으로구성된다. 여기에기재된적층물은, 차량또는건축용패널에사용될수 있다. 하나이상의구체예에서, 적층물은차량몸체의개구에배치될수 있다. 차량몸체가자동차인경우, 적층물은방풍유리, 사이드창, 선루프또는후방방풍유리로서사용될수 있다. 몇몇구체예의몸체는, 철도차량, 항공기또는선박을포함할수 있다. 다른구체예에서, 적층물은, 창, 내부벽 패널, 모듈식가구패널, 백스플래시, 캐비닛패널, 또는기기패널을포함할수 있는건축용패널에사용될수 있다. | ||||||
| 90 | 비상 상황 동력 보조 장치 | KR1020150029297 | 2015-03-02 | KR1020160106413A | 2016-09-12 | 민경무; 김준희; 마샬딥카프레; 빈현욱 |
| 본발명에따른비상상황동력보조장치는비상상황시항공기도어를개방하고, 상기항공기도어의댐핑력을제어할수 있는비상상황동력보조장치에있어서, 원통상의내부공간에가스를보관하는금속보틀, 상기금속보틀의일측에구비되어, 내부에형성된흡입밸브를통해상기금속보틀에가스를공급하는흡입블럭, 상기흡입블럭의일측에구비되어, 상기가스의압력을측정하는압력게이지, 상기금속보틀의타측에구비되어, 상기가스의배출구를폐쇄하고, 외부충격에의해파열되면서상기배출구를개방하는파열디스크, 상기파열디스크의일측에구비되어, 내부에형성된파열침이상기파열디스크를파열하여상기가스를상기금속보틀로부터토출시키는토출블럭, 상기토출블럭의일측에구비되어, 내부공간을따라왕복운동할수 있도록삽입설치된피스톤과상기피스톤에연장형성된액츄에이터샤프트를구비하는액츄에이터, 상기액츄에이터샤프트와연결설치되어, 상기액츄에이터샤프트의왕복운동에따라동작하는스누버샤프트와내부오일이유동하기위한우회유로를형성하는바이패스밸브가구비되어, 상기항공기도어의댐핑력을제어하는스누버를포함하여구성되는것을특징으로한다. | ||||||
| 91 | 윈드실드 와이퍼 시스템 | KR1020140144522 | 2014-10-23 | KR1020150051875A | 2015-05-13 | 밀러비탈리; 루이크롤란트 |
| 본발명은만곡된표면과, 중앙파크위치(A)를지닌진동하는기어드라이브(2)를가지는윈드실드(1)에관한윈드실드와이퍼시스템(3)에관한것이다. 상기시스템(3)은적어도하나의와이퍼암(13)과와이퍼블레이드(5)를포함하고, 상기와이퍼블레이드(5)는상기적어도하나의와이퍼암(13)에의해상기진동하는기어드라이브(2)에장착된다. 윈드실드(1)와와이퍼블레이드립(11)들은마찰계수(μ)를가진다. 2개의와이퍼암(13), 각각핏 볼트(20)를구비한 2개의와이퍼블레이드(5), 베어링부시(10)들, 연장피팅(7), 및로커(6)가제공된다. 상기 2개의와이퍼블레이드(5)는와이퍼블레이드회전축(9) 주위에서회전가능하게장착되며상기진동축(V) 및상기세로축(U)에수직이다. 상기와이퍼블레이드회전축(9)은서로에대해일정한거리(a)를두고본질적으로나란한상기 2개의와이퍼블레이드(5) 상에서서로마주보게장착된핏 볼트(20)들을통해중앙라인에의해규정된다. 회전가능한상기로커(6)는핏 볼트(20)에의해 2개의와이퍼블레이드(5) 각각을부착시킨다. 회전가능한상기연장피팅(7)은상기와이퍼암(13)에상기로커(6)를부착시킨다. 상기핏 볼트(12)는상기로커(6)를가지고상기진동축(V)과상기세로축(U)에의해규정된평면에서로커회전축(8)을규정하고, 상기중앙파크위치(A)에서의상기윈드실드(1)의외부표면에대한기울기각도(β)는 []<(1-μ)를만족시키는상기중앙파크위치(A)에서상기윈드실드(1)에수직인상기로커회전축(8)과상기윈드실드(1) 사이의와이퍼블레이드들회전축(9) 바로아래의거리(b)를제공한다. | ||||||
| 92 | 최적화된 외부 가시성을 구비한 조종실을 가지는 항공기와 방법 | KR1020140029871 | 2014-03-13 | KR1020140117276A | 2014-10-07 | 보드리장-피에르; 서튼니콜라스 |
| The present invention relates to an aircraft having a control compartment including a canopy provided with transparent surfaces fixed at bars; a central console; and two seats provided horizontally at one side of the central console. The aircraft includes at least one support (31, 33) connected to the central console; and at least one display unit to display multiple signs to help the operation of the aircraft. Each of the display units is supported by at least one support (31, 32, 33, 34) positioned between a theoretical position of eyes of a person sitting at one of the two seats and the bar. Each of the supports (31, 32, 33, 34) visually covers at least partially the bar to optimize visibility outside the control compartment to be used by people, and the theoretical position is determined by a manufacturer. | ||||||
| 93 | 후프 하중 지지 항공기 투명체 | KR1020137023581 | 2012-01-27 | KR1020130120543A | 2013-11-04 | 드가니스루이스이; 송디; 스튜어트셔먼디 |
| 후프 로드 베어링 항공기 투명체는 제 1 주 표면 및 제 2 주 표면을 갖는 제 1 플라이를 포함한다. 제 2 플라이는 제 1 플라이로부터 이격되어 있고, 제 3 주 표면 및 제 4 주 표면을 갖는다. 중합체 중간층은 제 1 플라이와 제 2 플라이의 사이에 위치한다. 적어도 하나의 보어가 제 1 플라이, 제 2 플라이 및 중간층을 통과하여 연장한다. 고강도 부싱이 보어의 안에 위치하고 부싱의 외측 측벽은 제 1 플라이 및 제 2 플라이의 재료와 직접 접촉한다. 일 실시예에서, 보어는 테이퍼 형상 보어이고 부싱은 테이퍼 형상 외측 측벽을 갖는다. 다른 실시예에서, 보어는 원통형 보어이고, 부싱은 원통형 외측 측벽을 갖는다.
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| 94 | 축소된 규모의 랜딩 기어 케이싱 | KR1020107000887 | 2008-05-28 | KR1020100040854A | 2010-04-21 | 게링베르나드; 생마끄로랑 |
| The invention relates to a landing gear casing that comprises a longitudinal box with walls defining an inner housing (24) open at the bottom and enabling the stowage of the landing gear (20) inside the housing and the deployment thereof outside the housing, the walls of the casing separating the non-pressurised inner housing from a surrounding pressurised area (18) of the aircraft, characterised in that the casing includes a primary inner frame including: several primary transverse reinforcement arcs (26, 28) inside the housing; at least one longitudinal central reinforcement arc (30a, 30b) inside the housing; wherein the walls of the casing and the reinforcement being adapted to conform to the shapes of the landing gear (20) and the stowage/expansion mechanism (22) thereof. | ||||||
| 95 | IMPROVED FRONT LANDING-GEAR WELL | PCT/FR2012052194 | 2012-09-27 | WO2013045852A3 | 2013-10-03 | GUERING BERNARD; DURAND YVES |
| The present invention relates to a front portion of an aircraft (1) including a fuselage (15) and a landing-gear well (22) housing a front landing gear (30) including a brace strut (36) designed such as to adopt an extended configuration when the landing gear is down, in which configuration said brace strut (36) is aligned with a strut plane (P1) parallel to the transverse direction (Y) of the front portion. According to the invention, the front portion includes a transverse beam (40) for taking up the forces from the strut, arranged above the landing-gear well (22) and mounted at the two ends thereof on the fuselage (15), the beam (40) having a generally rectangular cross-section in which the median plane (P2), parallel to the length of the rectangle, coincides with the strut plane (P1). | ||||||
| 96 | GUTTER PROFILE AND AIRCRAFT | PCT/EP2012058924 | 2012-05-14 | WO2012152947A2 | 2012-11-15 | GENSCH HINNIK; KIRSTEIN HAUKE |
| A gutter profile for draining liquids on an aircraft, comprising a connecting section for connecting the gutter profile to an outer skin of the aircraft and comprising a drain section for forming a drain cross-section of the gutter profile, where the drain section is pre-tensioned into a ground position which opens the drain cross-section and has a flow guiding device for transferring the drain section into a flight position which closes the drain cross-section, and an aircraft having such a gutter profile are disclosed. | ||||||
| 97 | IMPROVEMENTS IN AIRCRAFT DOORS | PCT/GB2006001554 | 2006-04-28 | WO2006114640B1 | 2006-12-21 | YARDLEY CHRISTOPHER; FARMER MICHAEL JOHN CHARLES |
| An alarm system for an aircraft door comprises; a sensor (22) for sensing when the door operating handle is about to be gripped by an operator, an aural alarm (35) associated with the sensor and operable to sound when the sensor detects that the handle is about to be gripped, means (32, 38) for receiving a signal activated in response to an event which occurs remote from the door and arming the sensor and/or aural alarm when the signal is received by the receiving means. | ||||||
| 98 | PIN LATCH WITH ADJUSTABLE PRE-LOAD | US16249971 | 2019-01-17 | US20190218837A1 | 2019-07-18 | Brody Wayne Collins; Bo D. Artin |
| A latch mechanism includes a handle connected to a pin by a linkage. The linkage converts rotation of the handle relative to a frame into axial movement of the pin between extended and retracted positions relative to the frame. | ||||||
| 99 | Wiper system with variable sweep angle motor drive | US15066690 | 2016-03-10 | US10106127B2 | 2018-10-23 | Santyar Srivatsa; Guru Prasad Mahapatra |
| A windshield wiper system for an aircraft is provided and includes a motor, an output shaft, a wrap spring and crank rocker mechanism (WSCRM) to which the motor and the output shaft are coupled and a controller. By way of the WSCRM, first directional rotation input to the WSCRM from the motor via a two-stage gear reduction is converted such that the output shaft drives wiper blade oscillation through a first sweep angle and second directional rotation input to the WSCRM from the motor is converted such that the output shaft drives wiper blade oscillation through a second sweep angle. The controller is configured to control the motor such that the first directional rotation is continuously or non-continuously input during first or second flight conditions, respectively, and the second directional rotation is continuously input during third flight conditions. | ||||||
| 100 | PUSH-OUT BUBBLE WINDOW FOR ROTARY AIRCRAFT | US15482594 | 2017-04-07 | US20180290723A1 | 2018-10-11 | Matthew John Hill; William David Tohlen; Bobby Howard Mosier; Lynn Francis Eschete |
| Aspects of the embodiments of the present disclosure are directed to a window panel having a bubble form. The window panel is a push-out window that permits emergency egress from an aircraft, such as a rotorcraft. The bubble form is designed and selected such that the window panel will remain secured in a window frame of the aircraft at a level cruising speed of 120 knots true air speed. In embodiments, the window panel remains secured in the window frame at 120 ktas and a sideslip of at least 6 degrees. | ||||||
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