| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | Aircraft of lining | JP2009546718 | 2008-01-18 | JP2010516550A | 2010-05-20 | ベンシーン，ヘルマン |
| 本発明は航空機のライニング１に関する。 ライニング１は圧密式で、航空機の中間空間６を内部空間７から分離する。 ライニングパネル３−５，４４，４５，６６は実質的に水平に広がり、又は胴体セル２の接続用に、プロファイル４７，６７によって形成されるライニングフレームワークに略垂直に固定される。
本発明により、少なくとも１つのライニングパネル３−５，４４，４５，６６は、内部空間７と中間空間６の間の自動的な均圧を許容し、結果的に、内部空間７内の圧力は０ｈＰａ（「急速減圧」として知られる）の桁に落ちる。 この圧力は１００００ｍより上の高度で行き亘る大気圧に対応する。 この目的のため、ライニングパネル３−５，４４，４５，６６のマウント４６，６８は、所定のブレーキングポイント３０，５９，７０と共に備えられる。 所定のブレーキングポイント３０，５９，７０は特に、プラスチックナット２８，５８，６９、限界荷重支持能を越えると離されるねじによって形成される。 【選択図】図１ |
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| 42 | Extension decompression flap structure | JP2008547859 | 2006-10-13 | JP2009522146A | 2009-06-11 | ラウル ライエンス |
| 本発明は、航空機、特に旅客機において、航空機の機体構造によって互いに分離され、且つ互いに対して空気圧力差を有する航空機の機体の領域間の急速な空気圧力平衡を作り出すための装置に関し、装置は、航空機の機体構造内の少なくとも１つの流通口と、流通口を少なくとも部分的に閉じる減圧フラップ（２６）と、臨界空気圧力差を越えるとき、減圧フラップ（２６）を、流通口が実質的に開く開位置に移動させることができるように、減圧フラップ（２６）を閉位置からロック解除するロック解除機構と、を含む。 本発明によれば、減圧フラップ（２６）は、互いにヒンジ連結された複数の部分を含む。 | ||||||
| 43 | Latch device of cockpit door of aircraft | JP2006306207 | 2006-11-13 | JP2008120245A | 2008-05-29 | SAKU FUMIAKI; WATANABE TADASHI; SEKIKAWA YASUO |
| <P>PROBLEM TO BE SOLVED: To prevent a cockpit door from unexpectedly opening by an impact, by providing a latch device releasing a bolt when pressure reduction in an aircraft is detected and a stopper device. <P>SOLUTION: A main latch device 100 of the cockpit door has a frame 112 fixed to a door panel, and a latch base 120 is mounted to the frame 112 capable of pivotal rotation with a pin 122 as a fulcrum. A bolt 132 is inserted into a catch in conjunction with a door handle 130. A holding/releasing portion 150 holds the latch base 120. When a pressure difference occurs between a cockpit 4 and a cabin 5, a pressure-sensing piston 160 is pushed in, a trigger 170 and a flapper 180 are rotated and the latch base 120 is released. A stopper device 190 regulates the movement of the trigger 170 by movement of an inertial piston 192 when an impact force is applied from the cabin 5 side. <P>COPYRIGHT: (C)2008,JPO&INPIT | ||||||
| 44 | Door to close the inside of the opening of the aircraft | JP2007524363 | 2005-07-18 | JP2008509038A | 2008-03-27 | フレンチ，クライブ; マクゼン，スマイル |
| 本発明は、一方の方向においては空気がドアを通過することを可能にするがこれとは反対の方向においてはこの通過を防止する装置を備えるドアに関する。 添付図面において、このドアは、空気を通過させる少なくとも１つの窓（７４）と、この窓（７４）を覆う弾性膜（７６）とを含む。 この弾性膜（７６）は、窓（７４）とは反対側にありかつこの窓を完全に覆うことが可能である空気非透過性区域と、この非透過性区域に隣接して配置されている空気透過性区域とを備える。 | ||||||
| 45 | Catching device of the cockpit door | JP2004077848 | 2004-03-18 | JP3806126B2 | 2006-08-09 | 隆春 大園; 誠一 富山 |
| 46 | Entrance apparatus for operator's compartment of transportation means, especially for cockpit of passenger plane | JP2003014659 | 2003-01-23 | JP2003237694A | 2003-08-27 | ROESSNER BERND; SPRENGER WILFRIED |
| <P>PROBLEM TO BE SOLVED: To provide an entrance apparatus for an operator's compartment, preferably for a cockpit of an airplane, that can minimize a space demand and a surface, attain simple constitution with minimized weight and guarantee pressure closed type isolation and a plurality of variable entrances/exits of the entrance apparatus. <P>SOLUTION: A safety sluice 1 is provided in an entrance region. The sluice is formed in cylindrical shape and rotatable within a frame structure body 2 around the vertical axis. The sluice 1 has a sluice entrance 11, and its opening part coincides with at least two entrance/exit sectors 21 of the frame structure body 2. The sluice entrance 11 is travelable to a previously selected sector position and lockable, and at the same time, all other entrance/exit sectors 21 are closed for the entrance/exit. <P>COPYRIGHT: (C)2003,JPO | ||||||
| 47 | Apparatus for supporting structure in aircraft or spacecraft | JP14889690 | 1990-06-08 | JPH0338498A | 1991-02-19 | BUORUFUHARUTO FUIRITSUTSU; ROOBERUTO FUINKUBAINERU; HAARARUTO KUNOOTE |
| PURPOSE: To provide a reliable device assembled at a low manufacturing cost by constituting a holding device with releasable mounting locks, applying its board and a flange to a wall section or a panel through a locking lever, and fixing the locking lever by a shearing safety device. CONSTITUTION: Each holding device is constituted as a releasable mounting lock 14, a board 18 and a flange on a frame are mounted on the opposite side and are applied to a wall section or a panel through at least a locking lever 23, and the locking lever 23 is oscillatingly mounted to the board 18 and fixed to a holding position with a shearing pin 24. In this structure, specific releasable pressure condition between the inside and the outside of the panel becomes adjustable by adequate sizing or material selection for the shearing pin 24 or by change of length of the locking lever 23. Because in operation of the releasable mounting lock 14, only a defined break of the shearing pin 24 is always provided instead of a break of the releasable mounting lock 14, providing of a target break position can be eliminated in sizing of the locking lever 23. COPYRIGHT: (C)1991,JPO | ||||||
| 48 | Device for limiting pressure difference, pressure balancing device, and aircraft equipped with this device | JP9862289 | 1989-04-18 | JPH0224296A | 1990-01-26 | FURANSHISU KARURA; BURUNO BARUU; JIYAAKU FUREESU; JIYAAKU SHINIYORE |
| PURPOSE: To quickly balance the pressure in the occurrence of trouble by providing a controlled valve whose fluid flow rate is adjustable by an instruction, providing at least one butterfly valve on the surface of the controlled valve, and providing a device for limiting the pressure difference in order to balance the pressure when the pressure difference between both sides of the butterfly valve exceeds a limit value. CONSTITUTION: The flow rate of a fluid passing a controlled valve 1 is related to the pressure difference between both sides of the controlled valve 1 and the surface opened by the controlled valve 1. A butterfly valve 2 is independently opened when the pressure difference between both the sides is larger than a limit value. The butterfly valve 2 is returned to the close position by two springs when the difference is smaller than the limit value of opening. The butterfly valve 2 is pivoted around a shaft 7. A motor 6 advances a rack with a rubber disc 9 according to an instruction, and the rubber disc 9 presses a flap 2' to close it. The rubber disc 9 seals the bulkhead of the butterfly valve 2. The rack can extend a rod 8 as long as the safety is to be maximized, and reaches the position of a bolt 11 in close position. COPYRIGHT: (C)1990,JPO | ||||||
| 49 | 航空機の水流入防止装置、航空機 | JP2012156195 | 2012-07-12 | JP6032980B2 | 2016-11-30 | 河野 慎吾; 真塩 知佳; 浦野 明崇; 萩野 修一 |
| 50 | Emergency ventilation method and system of the aircraft cabin in the case of a leak of ambient air mixer | JP2011536748 | 2009-09-08 | JP5559806B2 | 2014-07-23 | フランク クリンペル; リュトガー シュミット |
| 51 | Water inflow prevention device for aircraft, pressure control valve for aircraft and aircraft | JP2012156195 | 2012-07-12 | JP2014019174A | 2014-02-03 | KONO SHINGO; MASHIO CHIKA; URANO AKITAKA; HAGINO SHUICHI |
| PROBLEM TO BE SOLVED: To provide a device to prevent water from flowing into an aircraft through a pressure control valve at the time of emergency landing on the water without requiring operation by a pilot.SOLUTION: A closing lid 6 is installed to close a duct 2 of a pressure control valve 1 controlling atmospheric pressure in a cabin 101. A buoyancy body 9 is attached to the closing lid 6 which is a disk installed in the duct 2 so that the same can rotate around a rotation shaft 7. The buoyancy body 9 receives buoyancy of water when immersed in the water. Then, the buoyancy on a side of the closing lid 6 where the buoyancy body 9 attached thereto naturally rotates the same around the rotation shaft 7 and thereby closing a ventilation hole 2a. | ||||||
| 52 | Fire resistance bi-directional pressure reduction panel | JP2012544647 | 2010-12-09 | JP2013518752A | 2013-05-23 | フレッド ダブリュ． オップ; キース エー クルーガー |
| A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as a sidewall of an aircraft cargo compartment. During a decompression event, the pressure relief panel member is released bi-directionally in either of two opposing directions from the frame member when a predetermined pressure differential exists across the partition. The decompression panel assembly is fire resistant, and has reduced weight and fewer parts than prior conventional decompression panel assemblies. | ||||||
| 53 | Fire barrier for aircraft fuselage | JP2009508177 | 2007-04-26 | JP5134619B2 | 2013-01-30 | ライナー ミューラー |
| 54 | Internal security door of the aircraft | JP2007524362 | 2005-07-18 | JP4840877B2 | 2011-12-21 | フレンチ，クライブ; マクゼン，スマイル |
| 55 | Latch device of the cockpit door of an aircraft | JP2006306207 | 2006-11-13 | JP4263208B2 | 2009-05-13 | 文昭 佐久; 正 渡辺; 安雄 関川 |
| 56 | Internal security door in the aircraft | JP2007524364 | 2005-07-18 | JP2008509039A | 2008-03-27 | フレンチ，クライブ; マクゼン，スマイル |
| 本発明は、内部構造（１６）を形成する要素（２０、２１、２２、２４）を備えるドアに関する。 この内部構造（１６）は、内部構造を形成する要素の大部分を互いに連結するハーネスの網状物（８２）によって補強されている。 これらのハーネスは、例えば、内部構造上に接着されている炭素繊維のストリップである。 | ||||||
| 57 | Internal security door of the aircraft | JP2007524362 | 2005-07-18 | JP2008509037A | 2008-03-27 | フレンチ，クライブ; マクゼン，スマイル |
| 本発明は、２つの区画を備える内部構造物（１６）と、この区画の各々に取付けられたパネル（１８）と、対応する区画に各パネル（１８）を保持する手段とを備え、この手段が、所定の荷重が、所定の方向に、パネルに加えられる場合に、パネルを開放することを可能にする、ドアに関する。 | ||||||
| 58 | Cockpit door of an aircraft | JP2003015753 | 2003-01-24 | JP3971313B2 | 2007-09-05 | 裕宣 高濱 |
| 59 | Cockpit door of an aircraft | JP2003035958 | 2003-02-14 | JP3968031B2 | 2007-08-29 | 正 渡辺; 寿久 粕谷; 安雄 関川 |
| 60 | Cockpit door of an aircraft | JP2003344200 | 2003-10-02 | JP3947511B2 | 2007-07-25 | 文昭 佐久; 正 渡辺; 安雄 関川 |
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