| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 可破裂式板及其破裂方法以及车辆 | CN99104980.2 | 1999-04-09 | CN1214172C | 2005-08-10 | L·科利努斯 |
| 本发明提供一种可破裂式板，它构成位于通常封闭的内部环境与外部环境之间的隔离结构，其中所述板具有：至少一块可爆炸的炸药(7)，所述可爆炸的炸药安置在该板的至少部分中；包含在所述板内的纤维状保持结构(26)，用于在该可爆炸的炸药引爆后保持所述板的碎片。这样一来，所述炸药与引燃装置和/或引爆装置有效相连，以便引爆可爆炸的炸药，从而使板基本在其所处的平面内得到可控制地碎裂。本发明还提供了上述可破裂式板的破裂方法，它包括以下两个步骤：在所述板的至少部分内置入至少一块可爆炸的炸药，控制引爆所述可爆炸的炸药以便使该板基本在其所处平面内碎裂。本发明还涉及具有上述可破裂式板的车辆。 | ||||||
| 2 | 客机服务舱门空中应急开启时聚能切割器防护层复合材料 | CN200910025066.5 | 2009-02-16 | CN101486265B | 2010-11-03 | 王耀华; 金广谦; 顾月兵; 陆明; 龙源; 刘影; 周春华; 王兵; 马海洋 |
| 本发明公开了一种客机服务舱门空中应急开启时聚能切割器防护层复合材料。该防护层复合材料有两种构成方式：其一为由内向外的碳纤维布层、天然橡胶层和凯夫拉纤维布层通过环氧树脂粘结复合而成；其二为由内向外的碳纤维布层、凯夫拉纤维布层和聚氨酯层通过环氧树脂粘结复合而成。本发明通过纤维与橡胶的复合，能有效阻断爆炸冲击波的传播、降低噪声，且减小防护装置的自重，不会形成伤人的破片。所述的防护层贴合在聚能切割器的外壳表面，能够将爆炸次效应限制在最小范围内，适应了机舱内空间狭小的特点。 | ||||||
| 3 | 飞机紧急离机系统 | CN97199543.5 | 1997-10-03 | CN1087252C | 2002-07-10 | R·J·马丁; T·J·托纳 |
| 一种便于乘客/机组人员自一飞机(4)内紧急撤离的紧急离机系统(10)，该系统(10)包括一块出口板(12)，一个配置在出口板(12)周围的板框(14)和一根限定了背对背形式的沟槽(18)的挡风雨条(16)，该沟槽(18)用以接纳出口板(12)和板框(14)的周边(12E，14E)。此外，该紧急离机系统(10)包括若干保持装置(30)，它们配置在出口板(12)的周围，用以按正常操作模式将出口板(12)相对于板框(14)横向保持；一个凸轮装置(80)，可操作来强行使挡风两条(16)的一部分与周边(12E，14E)之一分离，一个驱动装置(50)，可操作来按顺序分离保持装置(30)中的至少一个，并按紧急操作模式驱动凸轮装置(80)。在驱动之后，乘客/机组人员可将出口板(12)跟板框(14)分离。 | ||||||
| 4 | 客机服务舱门空中应急开启时聚能切割器防护层复合材料 | CN200910025066.5 | 2009-02-16 | CN101486265A | 2009-07-22 | 王耀华; 金广谦; 顾月兵; 陆明; 龙源; 刘影; 周春华; 王兵; 马海洋 |
| 本发明公开了一种客机服务舱门空中应急开启时聚能切割器防护层复合材料。该防护层复合材料有两种构成方式：其一为由内向外的碳纤维布层、天然橡胶层和凯夫拉纤维布层通过环氧树脂粘结复合而成；其二为由内向外的碳纤维布层、凯夫拉纤维布层和聚氨酯层通过环氧树脂粘结复合而成。本发明通过纤维与橡胶的复合，能有效阻断爆炸冲击波的传播、降低噪声，且减小防护装置的自重，不会形成伤人的破片。所述的防护层贴合在聚能切割器的外壳表面，能够将爆炸次效应限制在最小范围内，适应了机舱内空间狭小的特点。 | ||||||
| 5 | 可破裂式板及其可控的破裂方法 | CN99104980.2 | 1999-04-09 | CN1238256A | 1999-12-15 | L·科利努斯 |
| 一种可破裂式板(2)，它构成位于通常封闭的内部环境与外部环境之间的隔离结构，例如汽车的多层窗，其体内包含有至少一块可爆炸的炸药(7)，炸药(7)与引燃装置和/或引爆装置有效地相连，以便引爆可爆炸的炸药，从而使板基本在其所处的平面内得到可控制地碎裂。 | ||||||
| 6 | 飞机紧急出口系统 | CN97199543.5 | 1997-10-03 | CN1236348A | 1999-11-24 | R·J·马丁; T·J·托纳 |
| 一种便于乘客/机组人员自一飞机(4)内紧急出口的紧急出口系统(10),该出口系统(10)包括一块出口板(12),一个配置在出口板(12)周围的板框(14)和一根限定背对背沟槽(18)的挡风雨条(16),该沟槽(18)用以接纳出口板(12)和板框(14)的周边(12E,14E)。此外,该紧急出口系统(10)包括若干保持装置(30),它们配置在出口板(12)的周围,用以按正常操作模式将出口板(12)相对于板框(14)侧向保持;一个凸轮装置(80),可操作来强行使挡风雨条(16)的一部分跟周边(12E,14E)之一分离,一个作动装置(50),可操作来按顺序分离保持装置(30)中的至少一个,并按紧急操作模式驱动凸轮装置(80)。在驱动之后,乘客/机组人员可将出口板(12)跟板框(14)分离。 | ||||||
| 7 | Emergency outlet in vehicle, particularly, aircraft and spaceship | JP23636987 | 1987-09-22 | JPS63149294A | 1988-06-22 | UERUNERU GURONOU |
| 8 | Emergency escape system for aircraft | JP52139398 | 1997-10-03 | JP2001503705A | 2001-03-21 | ジェイ． トナー，トーマス; ジェイ． ランダル，マーティン |
| (57)【要約】 航空機（４）から乗客／乗員の非常脱出を容易にする非常脱出システム（１０）は、脱出用パネル（１２）と、脱出用パネル（１２）の周囲に配置されたパネルフレーム（１４）と、脱出用パネル（１２）及びパネルフレーム（１４）の周辺端部（１２ E ，１４ E ）を受ける背中合わせのチャネル（１８）を画成するウエザーストリップ（１６）と、を含む。 非常脱出システム（１０）は、更に、通常運転モードにおいてパネルフレーム（１４）に対して脱出用パネル（１２）を横方向に保持するために脱出用パネル（１２）の周辺部にわたって配置された複数の保持装置（３０）と、非常運転モードにおいて力を加えることで周辺端部（１２ E ，１４ E ）の一方からウエザーストリップ（１６）の一部を分離するように動作可能なカム手段（８０）と、少なくとも１つの保持装置（３０）を順次分離させるとともにカム手段（８０）を動作させる作動手段（５０）と、を含む。 乗客／乗員は、作動後にパネルフレーム（１４）から脱出用パネル（１２）を分離することができる。 | ||||||
| 9 | Disruption of the polycarbonate and polycarbonate laminate according to the linear explosive | JP2001548331 | 2000-12-21 | JP2003518445A | 2003-06-10 | コロナ，セオドア・エフ; ヒルデン，リン・ジー; メンゼル，ダグラス・ディー; ワイス，レイモンド・ディー |
| (57)【要約】 本発明は、今日の軍用飛行機のキャノピーの多くが製造される材料のような、ポリカーボネート、ポリカーボネート積層体及びアクリル／ポリカーボネート積層体で出来た材料を分断する方法を対象とするものである。 搭乗員が脱出することを許容し得るように飛行機のキャノピーの一部分を分断する方法は、搭乗員の安全のため、必要である。 従来の分断方法は、キャノピー材料に又はその付近に或いはその内部に配置された爆薬によって発生された衝撃波を使用して材料を破砕することに重点が置かれていた。 これらの方法は、アクリル型式の材料で製造されたキャノピーを破砕するには効果的であるが、ポリカーボネート型式の材料を破断するには信頼性が欠ける。 本発明は、分断すべきポリカーボネート材料から所定の距離又は分離距離に配置された線形爆薬を利用する。 ポリカーボネート材料の所定の厚さを分断するのに必要な最小のコア負荷が利用されるように爆薬のコア負荷が決定される。 爆薬が材料から適正な分離距離にあるように、リテーナを爆薬の周りに配置し且つ材料に固着する。 リテーナは爆薬の後側を取り巻くが、爆薬と分断すべき材料との間に開放空間を残す。 爆裂したとき、爆薬がポリカーボネート材料を分断する爆発切断力すなわちジェット爆風を発生させる。 本発明はまた、分断すべきパターンの周りに爆薬を交差させる方法及びかかる交差する爆薬の間にて爆裂力を伝達する方法をも対象とする。 | ||||||
| 10 | Destroyed panel and removing method therefor | JP10246399 | 1999-04-09 | JP2000054751A | 2000-02-22 | COLLINUCCI LUCIANA |
| PROBLEM TO BE SOLVED: To provide a breaking panel which can be safely destroyed without scattering fragments during an emergency when an escape way becomes necessary. SOLUTION: A breaking panel 2 constituting a structural body for separating the internal environment from the external environment such as a laminated structural window used for a motor vehicle contain at least one explosive filler 7 inside. An ignition and (or) explosive device 8 is functionally coupled to the explosive filler 7 and, if this device ignites the explosive filler, then the panel 2 is essentially destroyed internally by a controlled method. COPYRIGHT: (C)2000,JPO | ||||||
| 11 | 항공기용 접이식 핸들 장치 | KR1020120033792 | 2012-04-02 | KR101310200B1 | 2013-09-24 | 김영우; 선석진 |
| PURPOSE: A foldable handle device for an airplane is provided to prevent accidents caused by malfunction and efficiently use the inner space of a pilot seat. CONSTITUTION: A foldable handle device (100) for an airplane comprises a torque shaft (150), a drive hub (H), a body part (110), a handle part (120), a stopper (130), and an elastic member (140). The drive hub is connected to one side of the torque shaft. The body part is coupled to the other side of the torque shaft. The handle part is coupled to the top of the body part through a rotary shaft (160). The stopper is arranged on the bottom of the handle part and is fixed to the body part to be not rotated by the torque shaft. The elastic member is arranged on the bottom of the body part and prevents the stopper from being separated from the body part. | ||||||
| 12 | AIRCRAFT CANOPY FRACTURE SYSTEM | PCT/US9903445 | 1999-02-18 | WO9942362A8 | 1999-10-14 | JAHSMAN HENDRICK E; HOPWOOD KEVIN M |
| An aircraft canopy fracturing system includes a canopy (170) having fore and aft positions and a region (176) that is severable from the canopy to provide an opening (181) therethrough for the egress of aircraft occupants. The severable region (176) has a shape that inhibits passage of the severable region through the opening (181) created in the canopy once the severable region is freed from the canopy and is displaced aftward relative to the canopy. The canopy fracturing system also may include one or more mechanisms that will impart an aftward impulse to the severable region of the canopy once it has been severed and freed from the remainder of the canopy. | ||||||
| 13 | WINDOW WITH AN EMERGENCY EXIT FUNCTION FOR A HELICOPTER AND METHOD FOR REMOVING A TRANSPARENT ELEMENT FROM THIS WINDOW | EP16187548.9 | 2016-09-07 | EP3293106B1 | 2018-11-14 | GORGOGLIONE, Giorgio; PAPALEO, Gaetano |
| A window (7) with an emergency exit function for a helicopter (1) is described that comprises: a frame shaped as a framework (8) that can be coupled to a door (6) of said helicopter provided with an opening (9); and a transparent element (10) designed to engage the opening (9) and held in position by the frame (8); the frame (8) comprises a first side (25) arranged abutting against the transparent element (10) when a first force (F) below a threshold value is exerted on the latter in a direction transversal to a first plane (P) of a main portion (11) of the transparent element (10), and which can be elastically moved away from the transparent element (10) when the first force (F) exerted on the latter exceeds the threshold value; and a second side (30) having greater flexural rigidity than the first side (25) in a second plane transversal to first plane (P) and arranged abutting against the transparent element (10) even when the force (F) is greater than said threshold value. | ||||||
| 14 | AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY | EP16185727.1 | 2016-08-25 | EP3263445A1 | 2018-01-03 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.
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| 15 | Aircraft with integrated jettison mechanism | EP13400004.1 | 2013-03-18 | EP2781451A1 | 2014-09-24 | Steger, Justus; Görlich, Stefan |
The invention relates to an aircraft (1) with jettison mechanism, particularly a helicopter, comprising an airframe (2), at least one door (5) with hinges to movably mount said at least one door (5) to the airframe (2), at least one door lock mechanism (9) at an interface of said at least one door (5) with the airframe (2) to releasable mount the at least one door (5) relative to the airframe (2) and actuation means (11) for the at least one door lock mechanism (9). An emergency button (20, 38) is integrated into handles (11, 12) of said actuation means.
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| 16 | Low profile jettisonable door system | EP13153927.2 | 2013-02-04 | EP2626294A3 | 2013-10-09 | Sumner, William P; Bookout, Philip J |
A jettisonable door system (101) for an aircraft (801) includes an upper hinge (149) having a forward portion that is hingedly coupled to an airframe (103) of the aircraft (801), the upper hinge (107) having an aft portion that is releasably secured to an upper outboard plate (140) with an upper pin (143). The jettisonable door system (101) further includes a lower hinge (137) having a forward portion that is hingedly coupled to the airframe of the aircraft (801), the upper hinge having an aft portion that is releasably secured to a lower outboard plate (123) with a lower pin (125). A rotation of the upper pin (143) releases the upper hinge (149) from the upper outboard plate (140) and a rotation of the lower pin (125) releases the lower hinge (137) from the lower outboard plate (123).
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| 17 | Emergency Jettison window pane and associated ejection system | EP09400032.0 | 2009-06-30 | EP2269857A1 | 2011-01-05 | Krahl, Kornelius |
The invention concerns an ejection system for a window pane (1) or panel which is affixed to a frame structure (2) with at least one clamping seal (3), comprising means for ejecting the panel or window pane (1) from the clamping seal (3), characterised in that it comprises: |
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| 18 | SEVERANCE OF POLYCARBONATES AND POLYCARBONATE LAMINATES WITH LINEAR SHAPED CHARGE | EP00993146 | 2000-12-21 | EP1292432A4 | 2004-02-04 | HILDEN LYNN G; MENZEL DOUGLAS D; WEISS RAYMOND D; CORONA THEODORE F |
| The present invention involves a method for severance of materials made of polycarbonate, polycarbonate laminate and acrylic/polycarbonate laminate, such as the materials from which many of today's military aircraft canopies are manufactured. A method of severing a section of an aircraft canopy so as to allow aircrew egress is necessary for aircrew safety. Past severance methods focused on fracturing materials using the shock waves created by explosive charges placed on, near or in the canopy material. These methods are effective for fracturing canopies manufactured from acrylic type materials, however, they are not reliable in severing polycarbonate type materials. The present invention utilizes a linear shaped explosive charge placed at a predetermined distance or stand off from the polycarbonate material to be severed. The coreload of the charge is determined such that the minimum coreload necessary to effect severance of a given thickness of polycarbonate material is utilized. A retainer is placed around the charge and affixed to the material such that the charge is at the proper stand off from the material. The retainer surrounds the back side of the charges but leaves open space between the charge and the material to be severed. Upon detonation, the charge creates an explosive cutting force, or jet blast, that severs the polycarbonate material. The present invention also involves methods for intersecting explosive charges about a pattern to be severed and methods for transferring detonation between such intersecting explosive charges. | ||||||
| 19 | EMERGENCY EGRESS SYSTEM FOR AIRCRAFT | EP97946241.0 | 1997-10-03 | EP0935556A1 | 1999-08-18 | RANDALL, Martin, J.; TONER, Thomas, J. |
| An emergency egress system (10) for facilitating emergency egress of passengers/crewmembers from an aircraft (4), which egress system (10) includes an egress panel (12), a panel frame (14) disposed about the egress panel (12) and a weather strip (16) defining back-to-back channels (18) for accepting the peripheral edges (12E, 14E) of the egress panel (12) and the panel frame (14). Furthermore, the emergency egress system (10) includes a plurality of retention devices (30) disposed about the periphery of the egress panel (12) for laterally retaining the egress panel (12) with respect to the panel frame (14) in a normal operating mode, a cam means (80) operative to forcibly urge a portion of the weather strip (16) out of engagement with one of the peripheral edges (12E, 14E) and an actuation means (50) operative to sequentially disengage at least one of the retention devices (30) and actuate the cam means (80) in an emergency operating mode. Following actuation, a passenger/crewmember may detach the egress panel (12) from the panel frame (14). | ||||||
| 20 | Notausgang an Fahrzeugen, insbesondere Luft- und Raumfahrzeugen | EP87109930.5 | 1987-07-10 | EP0261329B1 | 1990-11-07 | Gronow, Werner |
