子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | 複合材構造 | JP2014116041 | 2014-06-04 | JP2015229276A | 2015-12-21 | 杉山 拓史; 清水 隆之; 阿部 俊夫 |
| 【課題】発熱体から熱を受ける場合、熱の滞留を抑制しつつ、外力による破損を抑制することができる複合材構造を提供する。 【解決手段】複合材構造1は、発熱体24に対向して配置され、PAN系炭素繊維を含む第1複合部材21と、発熱体24と第1複合部材21との間に配置され、ピッチ系炭素繊維を含む第2複合部材22と、第1複合部材21と第2複合部材22との間に設けられ、第1複合部材21及び第2複合部材22にそれぞれ接合されると共に、第1複合部材21及び第2複合部材22よりも低剛性となる緩衝体23と、を備え、第1複合部材21は、隣接する構造体25に連結して設けられる一方で、第2複合部材22及び緩衝体23は、構造体25と分離して設けられる。 【選択図】図2 |
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| 162 | 帯域幅抑圧を増加した音響構造 | JP2015511554 | 2013-05-03 | JP2015520871A | 2015-07-23 | アイル、アール |
| 単独で利用されるいずれかの音響セルの有効音響長又は有効共振器長の最大2倍の有効音響長又は有効共振器長を有する音響セルの対を形成するため、ハニカム・セルを音響的に一緒に結合することにより、エンジン室又は他のタイプの音響構造の帯域幅又は音響範囲が増加される。 | ||||||
| 163 | Fire protection wall of aircraft, pylon, and aircraft | JP2013011745 | 2013-01-25 | JP2014141202A | 2014-08-07 | TAKEUCHI HIROSHI |
| PROBLEM TO BE SOLVED: To provide a fire protection wall capable of preventing flame from passing through fastener holes without using sealant for connection parts of members in which the through holes are formed.SOLUTION: A fire protection wall 50 is capable of preventing flame from leaking from a connection part connecting a first member 51 and a second member 55, particularly from fastener holes TH. Specifically, the connection part belongs to a fire protection chamber 52, and even if flame reaches a seal piece 51d or a seal piece 51e, flame cannot enter a closed space CA because the seal piece 51d and the seal piece 51e contact each other. Therefore, since flame does not reach the connection part, flame does not leak from the fire protection wall 50 and furthermore from a nacelle 23 to the outside. | ||||||
| 164 | System and method for minimizing wave drag through bilaterally asymmetric design | JP2013237617 | 2013-11-18 | JP2014104973A | 2014-06-09 | WILLIAM PFLUG; TILLOTSON BRIAN J |
| PROBLEM TO BE SOLVED: To provide an aircraft configuration that minimizes wave drag.SOLUTION: An air vehicle 100 having a bilaterally asymmetric configuration includes a body 104 having a longitudinal axis. The air vehicle further includes longitudinally offset engine nacelles 152, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces 268. | ||||||
| 165 | Nacelle | JP2013032773 | 2013-02-22 | JP2013173524A | 2013-09-05 | JAMES NORMAN JOHN |
| PROBLEM TO BE SOLVED: To provide a nacelle that minimizes drag forces on an aircraft and allows for easy access to the inside of the nacelle.SOLUTION: A nacelle 116 includes a first cowling 128 that partially defines an inlet 119 of the nacelle 116 and at least partially defines an outlet 131 of the nacelle 116. The first cowling 128 includes a unitary portion that extends continuously from the inlet 119 to the outlet 131. The nacelle 116 also includes a second cowling 126 that at least partially defines the inlet 119 and moves to the first cowling 128. The nacelle 116 can include a third cowling 130 that at least partially defines the outlet 131 and moves to the first cowling 128. | ||||||
| 166 | Integration engine nacelle structure | JP2013502697 | 2011-03-28 | JP2013527894A | 2013-07-04 | パトリック ジェー． スラッシュ，; デーヴィッド マイケル ミラー， |
| エンジンナセルの内側バレル構造。 内側バレル構造は、内側外板、複数の空洞を定めるために内側外板に対して配置されるトラスコア、及びそれぞれが空洞に配置される複数のセプタムを有する。 | ||||||
| 167 | Aircraft engine cowl and production process therefor | JP2012122586 | 2012-05-30 | JP2012251552A | 2012-12-20 | SCARR ANTONY BRETT |
| PROBLEM TO BE SOLVED: To provide a cowl for an aircraft engine, and processes for producing the cowl to have a layered construction and high temperature capability.SOLUTION: The layered construction of the cowl 136 includes a core member 144 having a cellular construction comprising internal hollow cells 148, and first and second skins 140,142 brazed to edges 152 of the cells 148 at opposite surfaces of the core member 144. The first and second skins 140,142 and the core member 144 are formed of titanium alloys, the first and second skins 140,142 are brazed to the core member 144, and the layered construction of the cowl 136 lacks a thermal insulation capable of thermally protecting the second skin 142 and brazed joints 150 that attach the second skin 142 to cell wall edges 152 at the second surface of the core member 144. | ||||||
| 168 | Wireless engine monitoring system | JP2010090466 | 2010-04-09 | JP2010209916A | 2010-09-24 | ZIARNO JAMES J |
| <P>PROBLEM TO BE SOLVED: To provide a wireless engine monitoring system which is advantageous that engine real time monitoring is performed without relying on a large-scaled ground data link unit having an interface with numerous systems, namely, it is performed by a smaller unit when a conventional ground data link unit cannot be utilized. <P>SOLUTION: The wireless engine monitoring system (WEMS) is directly mounted on an aircraft engine, and records, preserves, encodes, and transmits all flight engine data. It is preferable that the wireless engine monitoring system has an interface to a full authority digital engine controller/an engine control unit (FADEC/ECU) and it can record hundreds of engine parameters at desirable sampling frequency of about one second. An engine monitoring module is preferably formed as a miniaturized module wherein the engine monitoring system is directly mounted in a cowling of the aircraft engine, and has a conformal antenna. The monitoring module can also upload data for processing on board. <P>COPYRIGHT: (C)2010,JPO&INPIT | ||||||
| 169 | Beads with soundproof panel and a method of manufacturing the same | JP2004334017 | 2004-11-18 | JP4057008B2 | 2008-03-05 | アラン・ドラベ; オスマン・デルベルデイエ; ジヤツク・ジユリアール; ジヨルジユ・リウ; フイリツプ・ビー |
| The panel has a core with cells separated by partitions (12) fixed to nonporous and porous walls (6, 8). Each cell is divided by a sound energy dissipating layer (14). The layers are constituted of spherical balls with porous and micro-perforated walls. The balls are supported between the walls (6, 8) by threads (22) that have same composition as that of the partitions. The layers have constant/variable thickness in the same cell. The balls are in mutual contact, inside the sound energy dissipating layers. The threads are fixed against the partitions. An independent claim is also included for a method of producing a sound damping panel. | ||||||
| 170 | Engine monitoring system by radio | JP2006521081 | 2004-06-28 | JP2007516377A | 2007-06-21 | ジャーノ，ジェイムズ，ジェイ |
| 航空機エンジンに直接取り付けられ、全飛行エンジンデータを記録し、保存し、暗号化し、送信する無線エンジン監視システム（ＷＥＭＳ）。 当該システムは好ましくは、完全統括デジタルエンジン制御器／エンジン制御ユニット（ＦＡＤＥＣ／ＥＣＵ）へのインターフェースをもち、何百ものエンジンパラメータを、約１秒の好ましいサンプリング周波数で記録できる。 エンジン監視モジュールは好ましくは航空機エンジンのカウリング内に直接取り付けられる小型化されたモジュールとして形成され、コンフォーマルアンテナを有する。 監視モジュールは機上処理のためにデータをアップロードすることもできる。 | ||||||
| 171 | Fine jet-controlled sound absorption system | JP2001202953 | 2001-07-04 | JP3809520B2 | 2006-08-16 | 達哉 石井 |
| The fine jet control type sound absorption system of this invention, aimed at absorbing low-frequency sound with both discrete frequency and broadband frequency to the same degree as already existing acoustic lining can do, is composed of two parts. One is a barrier wall covering an air space in which the concerning low-frequency sound propagates and having a multiplicity of small holes formed therein. The other is the means for causing a fine jet passing through these small holes into or out from the air space. This sound absorption system realizes a fine jet in the vicinity of the barrier wall for the purpose of canceling the sound inside the air space by means of the interference of the sound with the fine jets. Any of or a combination of shape of small holes, jet ejection angle or suction angle, amount of jet flow, thickness of a barrier wall back layer and air flow angle at which secondary air flows into the barrier wall back layer is selected. | ||||||
| 172 | Hybrid laminar flow nacelle | JP12017190 | 1990-05-11 | JPH0737240B2 | 1995-04-26 | ダニエル・ジョン・ラッチ; デビット・イージン・ヤッテ; ノーベルト・オグデン・ストックマン; パーマナンド・マンガー |
| A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between the surfaces and a tailored outer surface geometry shape for producing reduced friction drag laminar flow over the outer cowl at cruise operation of the aircraft and producing separation-free flow over the inner surface of the cowl at off-cruise operation of the aircraft. | ||||||
| 173 | JPH06510724A - | JP50592892 | 1992-09-23 | JPH06510724A | 1994-12-01 | |
| 174 | JPH03501835A - | JP51001489 | 1989-09-27 | JPH03501835A | 1991-04-25 | |
| 175 | Ventilation system for nacelle | JP28659188 | 1988-11-12 | JPH0223257A | 1990-01-25 | ROBAATO BUBERO; JIEFURII IN RIIMU |
| PURPOSE: To improve exhaust efficiency by forming pressure relief holes in a nacelle surrounding a gas turbine engine, wherein a door for opening and closing the pressure relief hole as a pressure in the nacelle increases is pivotally supported by a hinge at the upstream of the hole. CONSTITUTION: A nacelle 14 surrounding a gas turbine engine 12 for aircrafts is composed of a fan nacelle 16 and a core nacelle 18. The core nacelle 18 has a nacelle wall 34 and the fan nacelle 16 has an inner wall 36. An annular fan bypass passage 38 is formed in a gap between the inner wall 36 and a fan chamber radially spaced from the inner side of the inner wall 36. Further, the core nacelle 18 is provided with a pair of pressure relief holes 48 in the nacelle wall 34. In this case, each of the relief holes 48 is provided with a relief door 50 pivotally supported by a hinge at the upstream of the hole 48. As the pressure in the nacelle 14 increases the door 50 is rotated from a fully closed position via a pressure equilibrium position to a fully opened position. COPYRIGHT: (C)1990,JPO | ||||||
| 176 | Turbofan-engine with split type cowling | JP4769088 | 1988-03-02 | JPS63246454A | 1988-10-13 | AASAA POORU ADAMUSON |
| 177 | Casing | JP10792287 | 1987-04-30 | JPS62276202A | 1987-12-01 | PRESZ JR WALTER M; PATERSON ROBERT W; WERLE MIACHAEL R |
| 178 | Generation of nacelle and contour thereof | JP19106083 | 1983-10-14 | JPS5996462A | 1984-06-02 | DANIERU JIYON RAHATEI; JIEIMUSU RUROI YANGUHANSU |
| 179 | JPS5037198A - | JP7375074 | 1974-06-27 | JPS5037198A | 1975-04-07 | |
| 180 | 棘爪闩锁 | CN201720087084.6 | 2017-01-23 | CN206503451U | 2017-09-19 | 泰·都 |
| 一种棘爪闩锁，具有带销的销组件和适于接收销组件的接收器组件。接收器组件包括：接收器外壳，其具有可滑动地定位在接收器外壳上的滑动件；可旋转地安装在接收器外壳中的凸轮；以及连接凸轮和滑动件的连杆。旋转凸轮使得滑动件沿接收器外壳移动。接收器组件包括棘爪和止动件，各自具有旋转的臂。当接收器组件接收销组件时，接触止动件的臂并且促进它们的旋转，其中凸轮能够被旋转，并且继而促进滑动件的移动。棘爪的臂被旋转以便将销组件的销头部锁定在接收器组件内。 | ||||||
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