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61. 发明申请

US20080179459A1 Pressure bulkhead made of composite material for an aircraft 审中-公开
标题翻译：用于飞机的复合材料制成的压力舱壁
公开(公告)号：US20080179459A1
公开(公告)日：2008-07-31
申请号：US11699743
申请日：2007-01-30
申请人： Agustin Garcia Laja , Francisco Jose Cruz Dominguez
发明人： Agustin Garcia Laja , Francisco Jose Cruz Dominguez
IPC分类号： B64C1/10 , B23P25/00
CPC分类号： B64C1/10 , Y10T29/49885 , Y10T156/1043
摘要： The present invention relates to a curved rear pressure bulkhead (1) made of a composite material, comprising three layers: an outer layer (2) and an inner layer (3) symmetrical with one another, which are made of a fiber laminate, and the intermediate layer or core (4) made of a lightweight material. With such a sandwich-type shape, the resulting bulkhead (1) is able to withstand the bending loads coming from the strain and pressurization of the fuselage without having to increase its stiffness by means of using some type of stiffener. The bulkhead (1) comprises a ring (6) that is attached to the ends of the sandwich shape. This ring (6) is split into several parts (8) to facilitate the assembly of the bulkhead (1) made of composite material to the fuselage skin (5).
摘要翻译：本发明涉及一种由复合材料制成的弯曲后压舱壁（1），包括三层：由纤维层压制成的外层（2）和彼此对称的内层（3），以及中间层或由轻质材料制成的芯（4）。通过这种夹层型形状，所得的隔板（1）能够承受来自机身的应变和加压的弯曲载荷，而不必通过使用某种类型的加强件增加其刚度。隔板（1）包括附接到夹心形状的端部的环（6）。该环（6）被分成若干部分（8），以便于由复合材料制成的隔板（1）组装到机身皮肤（5）上。

62. 发明申请

US20070138340A1 Protective skin for aircraft 有权
标题翻译：飞机保护皮肤
公开(公告)号：US20070138340A1
公开(公告)日：2007-06-21
申请号：US10568171
申请日：2003-08-27
申请人： Husam Arafat , Aldo Villa
发明人： Husam Arafat , Aldo Villa
IPC分类号： B64C1/10
CPC分类号： B64C3/28 , B64C2003/146
摘要： A protective skin (143a, 143b) for an aircraft is disclosed. The protective skin (143a, 143b) forms the leading edges of wing members, horizontal stabilizers, and vertical fins. A portion of the skin material (143a, 143b) is removed in a selected pattern (155a, 157a, 159a, 161a, 155b, 157b, 159b, 161b) from the interior surface of the skin (143a, 143b). In the preferred embodiment, the interior surface of the skin is chemically etched and/or mechanically milled in oval and rectangular patterns so as to create crumple zones (155a, 157a, 159a, 161a, 155b, 157b, 159b, 161b) and generate progressive failure of the metal. This allows the leading edge to absorb the impact energy from a collision with a bird or other object, and prevent the bird or other object from penetrating through the leading edge into the substructure.
摘要翻译：公开了一种用于飞行器的保护皮肤（143a，143b）。保护皮肤（143a，143b）形成翼部件，水平稳定器和垂直翅片的前缘。一部分皮肤材料（143a，143b）以选定的图案（155a，157a，159a，161a，155b，157b，159b，161b）从所选择的图案皮肤（143 a，143 b）。在优选实施例中，皮肤的内表面被化学蚀刻和/或以椭圆形和矩形图案机械研磨，以便产生褶皱区域（155a，157a，159a，161a，155b，157b，159a b，161b）并且产生金属的渐进失效。这允许前缘吸收与鸟或其他物体碰撞的冲击能量，并且防止鸟或其他物体穿过前缘进入子结构。

63. 发明申请

US20060145009A1 Penetration- and fire-resistant fabric materials and structures 审中-公开
标题翻译：穿透和防火织物材料和结构
公开(公告)号：US20060145009A1
公开(公告)日：2006-07-06
申请号：US11090645
申请日：2005-03-25
申请人： Donald Shockey , David Erlich , Jeffrey Simons
发明人： Donald Shockey , David Erlich , Jeffrey Simons
IPC分类号： B64C1/10
CPC分类号： B64C1/066 , B32B5/02 , B32B5/022 , B32B5/26 , B32B15/14 , B32B2250/40 , B32B2262/0253 , B32B2262/0269 , B32B2307/304 , B32B2307/3065 , B32B2307/536 , B32B2307/552 , B32B2307/558 , B32B2307/714 , B32B2571/02 , B32B2605/18 , B64C1/12 , B64D7/00 , F41H5/04 , F41H5/0471 , F41H7/00
摘要： A ballistic and/or fire barrier for protecting objects in an interior of a vehicle due to projectile penetration and/or fire includes one or more layers of high strength fabric positioned towards an outer shell of the vehicle. The high strength fabric is substantially fixedly or fixedly positioned with respect to the outer shell of the vehicle. In another embodiment, the ballistic and/or fire barrier protects objects in a structure from damage due to projectile penetration. The ballistic and/or fire barrier includes at least one layer of high strength fabric positioned towards an outer housing of the structure. The high strength fabric is substantially fixedly positioned with respect to the structure towards either the inner or outer surface of the outer housing. In another embodiment of the present invention, a ballistic barrier protects a wearer of the ballistic barrier from damage due to projectile penetration. The ballistic barrier comprises first and second portions positioned generally parallel each other. The first portion includes one or more layers of high strength fabric while the second portion is generally impact-resistant. Preferably, the layer of high strength fabric comprise a plurality of plies. One of the plies can comprise woven fibers. Another of the plies can be a felt. Also preferably, the layer of high strength fabric in the ballistic barrier embodiments comprises a polymer material such as one or more of aramid material, polyethylene material, and polybenzoxazole material.
摘要翻译：用于保护由于射弹穿透和/或火引起的车辆内部物体的弹道和/或防火屏障包括朝向车辆的外壳定位的一层或多层高强度织物。高强度织物相对于车辆的外壳基本固定或固定地定位。在另一个实施例中，弹道和/或防火屏障保护结构中的物体免受由弹丸穿透引起的损坏。弹道和/或防火屏障包括朝向结构的外壳定位的至少一层高强度织物。高强度织物相对于结构基本上固定地定位到外壳的内表面或外表面。在本发明的另一个实施例中，防弹屏障保护防弹屏障的佩戴者免受由于射弹穿透的损害。防弹屏障包括大致平行彼此定位的第一和第二部分。第一部分包括一层或多层高强度织物，而第二部分通常是抗冲击的。优选地，高强度织物层包括多个层。其中一层可以包括编织纤维。另一层可以是感觉。还优选地，防弹实施例中的高强度织物层包括聚合物材料，例如芳族聚酰胺材料，聚乙烯材料和聚苯并恶唑材料中的一种或多种。

64. 发明申请

US20050279886A1 Jittie Blocker / Shield 审中-公开
公开(公告)号：US20050279886A1
公开(公告)日：2005-12-22
申请号：US10709233
申请日：2004-04-22
申请人： Edward Willis
发明人： Edward Willis
IPC分类号： B64C1/10 , B64C1/14 , B64D11/00 , B64D45/00
CPC分类号： B64D45/0015 , B64C1/10 , B64C1/1469
摘要： An aircraft cockpit reinforced, stationary dividing wall system that completely separates the Pilots cockpit flight deck from the passengers compartment. Additionally, this stationary dividing wall shall be an engineered unit consisting of Titanium studding, thick Titanium plates, attached on each side with an outer thick layer of Kevlar and a material called spectra. This stationary dividing wall shall be designed to maintain complete separation of the passengers from the aircraft navigation personnel. The lightweight, solid, bulletproof, stationary interior enclosing wall system, wherein with relatively few components, most of which can be formed from titanium sheet stock. A wide variety of interior full height walls can be constructed, thus avoiding the necessity of the manufacture and inventory of a large number of parts. In the preferred form, a verticalness panel is constructed having rolled formed recessed edge that includes a folded flange of special configuration uniformly spaced, so that the wall studding and panels may readily be secured with rivets. The studs would be attached to the frame assembly that support the fuselage skin panels and would become a part of said frame structure. A nonwoven mix of Kevlar and a material called Spectra would accommodate a wide variety of surface finishes and provide and appearance cover for stopping bullets and similar high impact force projectiles.
摘要翻译：飞机驾驶舱加固的分隔墙系统，将飞行员驾驶舱驾驶舱与乘客舱完全分开。另外，这个固定的分隔壁应该是一个工程单位，由Titanium镶嵌，厚钛板，两边都有Kevlar的外部厚层和称为光谱的材料组成。该固定分隔墙应设计成保持乘客与航空器导航人员的完全分离。轻质，坚固，防弹，固定的内封壁系统，其中组件相对较少，其中大部分可以由钛片材制成。可以构建各种各样的内部全高的墙壁，从而避免了制造和库存大量零件的必要性。在优选形式中，垂直板被构造成具有卷成形的凹入边缘，其包括均匀间隔的特殊构造的折叠凸缘，使得壁布和面板可以容易地用铆钉固定。螺柱将附接到支撑机身蒙皮面板的框架组件，并且将成为所述框架结构的一部分。 Kevlar和名为Spectra的材料的非织造混合物将适应各种表面光洁度，并提供用于阻止子弹和类似的高冲击力射弹的外观盖。

65. 发明授权

US06896224B1 Apparatus and method for mitigating toe strike in aircraft 失效
标题翻译：减轻飞机趾部撞击的装置和方法
公开(公告)号：US06896224B1
公开(公告)日：2005-05-24
申请号：US10807577
申请日：2004-03-18
申请人： John L. Goodwin
发明人： John L. Goodwin
IPC分类号： B60R21/16 , B60R21/206 , B64D25/10 , B64C1/10
CPC分类号： B64D25/10 , B60R2021/23176 , B64D2201/00
摘要： A method for mitigating toe strike in a cockpit of an aircraft includes providing an airbag module attached to an instrument console located in the cockpit of the aircraft; releasing an airbag from the airbag module after an ejection sequence begins; using the airbag to protect a pilot's lower limbs from striking the instrument console as the pilot begins ejecting.
摘要翻译：一种用于减轻飞机驾驶舱中的脚趾撞击的方法包括提供安装在位于飞行器驾驶舱中的仪表控制台的气囊模块; 在喷射顺序开始之后，从气囊模块释放气囊; 当飞行员开始喷射时，使用安全气囊来保护飞行员的下肢免于撞击仪表控制台。

66. 发明授权

US06868314B1 Unmanned aerial vehicle apparatus, system and method for retrieving data 失效
标题翻译：无人驾驶飞行器具，检索数据的系统和方法
公开(公告)号：US06868314B1
公开(公告)日：2005-03-15
申请号：US10186154
申请日：2002-06-27
申请人： Bentley D. Frink
发明人： Bentley D. Frink
IPC分类号： B64C1/00 , B64C1/06 , B64C1/10 , B64C39/02 , B64D47/02 , H05K1/02 , H05K1/18 , B64C1/16
CPC分类号： H05K1/02 , A01K79/00 , B64C1/00 , B64C39/024 , B64C2201/021 , B64C2201/044 , B64C2201/086 , B64C2201/104 , B64C2201/125 , B64C2201/145 , B64C2201/165 , B64C2201/187 , B64D47/02 , H05K1/181 , H05K2201/09145
摘要： The present invention relates to a system for retrieving data from remote difficult to reach terrain, such as wilderness areas, etc. and in particular to a system comprised of one or more surface based data collectors in communication with one or more wireless transceivers adapted to transmit the collected data to an unmanned aerial vehicle adapted to fly within a predetermined distance from the data collector and receive data collected therefrom. The present invention further relates to an unmanned aerial vehicle adapted to fly a flight pattern relative to a moveable surface object or for controlling the position of a moveable surface object relative to the flight path of the unmanned aerial vehicle. Finally, the present invention relates to an improved unmanned aerial vehicle having airframe structural elements with electrical circuits adhered to the surfaces of the structural elements.
摘要翻译：本发明涉及一种用于从远程难以达到的地形（例如荒野区域等）检索数据的系统，特别涉及一种由一个或多个基于表面的数据收集器组成的系统，该系统与一个或多个适于发送的无线收发器通信将收集的数据传送到适合于从数据收集器预定距离内飞行并接收从其收集的数据的无人驾驶飞行器。本发明还涉及一种适于相对于可移动表面物体飞行飞行图案或用于控制可移动表面物体相对于无人驾驶飞行器的飞行路径的位置的无人驾驶飞行器。最后，本发明涉及一种具有机身结构元件的改进的无人驾驶飞行器，其中电路被粘附到结构元件的表面。

67. 发明申请

US20050045766A1 FORM FACTORED COMPLIANT METALLIC TRANSITION ELEMENT FOR ATTACHING A CERAMIC ELEMENT TO A METALLIC ELEMENT 有权
标题翻译：用于将陶瓷元件连接到金属元件的形成合适的合金金属过渡元件
公开(公告)号：US20050045766A1
公开(公告)日：2005-03-03
申请号：US10313713
申请日：2002-12-04
申请人： Quenten Duden , Wayne Sunne , James Gottlieb
发明人： Quenten Duden , Wayne Sunne , James Gottlieb
IPC分类号： H01Q1/28 , H01Q1/42 , B64C1/10
CPC分类号： H01Q1/42 , H01Q1/28
摘要： A ceramic element, e.g., a sapphire dome, is joined to a metallic element, e.g., a vehicle body comprising a titanium alloy, by an attachment structure, e.g., comprising niobium. The attachment structure comprises: (1) a form-factored, compliant metallic transition element having a “C” shape; (2) a first joint material connecting an upper portion of the transition element to the ceramic element; and (3) a second joint material connecting a lower portion of the transition element to the metallic element. A method is provided for attaching the ceramic element to the metallic element, using a single brazing operation. The presence of the attachment structure further minimizes the stresses related to the different coefficients of thermal expansion in the ceramic/attachment/titanium connection.
摘要翻译：诸如蓝宝石圆顶的陶瓷元件通过诸如包含铌的附接结构连接到金属元件，例如包括钛合金的车体。附件结构包括：（1）具有“C”形状的形状因子兼容的金属过渡元件; （2）将过渡元件的上部连接到陶瓷元件的第一接头材料; 和（3）将过渡元件的下部连接到金属元件的第二接头材料。提供了一种使用单个钎焊操作将陶瓷元件附接到金属元件的方法。附着结构的存在进一步使与陶瓷/连接/钛连接中的不同热膨胀系数有关的应力最小化。

68. 发明授权

US6138949A Main rotor pylon support structure 有权
标题翻译：主转塔吊架结构
公开(公告)号：US6138949A
公开(公告)日：2000-10-31
申请号：US183758
申请日：1998-10-30
申请人： Lawrence Manende , Robert N. Herkimer
发明人： Lawrence Manende , Robert N. Herkimer
IPC分类号： B64C1/10 , B64C27/04
CPC分类号： B64C1/10 , B64C1/00 , B64D33/02 , B64C27/04
摘要： A helicopter main rotor pylon support structure including a framing structure for supporting the loads applied to the main rotor pylon, and a fire shield for preventing fire from transmitting from an engine or exhaust compartment into an adjacent compartment. The framing structure includes first and second composite main beams, each beam extending adjacent to a engine compartment and an exhaust duct compartment. A plurality of bridge members preferably extend between and connect with the first and second main beams and are formed integral therewith. A plurality of vertical posts are attached to and spaced along the main beams. The vertical posts are engaged with discrete attachment points on the helicopter. There is at least one fire panel mounted to each main beam. The fire panel has side edges which are slidingly engaged with the vertical posts, and a lower edge which is slidingly engaged with a flange formed on the helicopter. The sliding engagement of the edges of the fire panel is designed to allow in-plane motion of the panel edges while limiting out-of-plane displacements. The sliding engagements are also designed to prevent the transmission of fire past the fire panel.
摘要翻译：直升机主转子塔架支撑结构，其包括用于支撑施加到主转子塔的负载的框架结构，以及用于防止火从发动机或排气室传递到相邻隔室中的防火罩。框架结构包括第一和第二复合主梁，每个梁相邻于发动机舱和排气管道隔间延伸。多个桥构件优选地在第一和第二主梁之间延伸并与第一和第二主梁连接，并且与其形成一体。多个垂直柱附接到主梁并且沿主梁间隔开。垂直杆与直升机上的离散附接点接合。至少有一个防火板安装在每个主梁上。防火板具有与竖直柱滑动接合的侧边缘，以及与形成在直升机上的凸缘滑动接合的下边缘。防火板的边缘的滑动接合被设计成允许面板边缘的平面内运动，同时限制了平面外的位移。滑动接合也被设计成防止火通过防火板传播。

69. 发明授权

US5979826A Hybrid composite article and missile components and their fabrication 失效
标题翻译：混合复合制品和导弹部件及其制造
公开(公告)号：US5979826A
公开(公告)日：1999-11-09
申请号：US108581
申请日：1998-07-01
申请人： Janis Brown , Ron Allred , Tom Duncan , Andrew Facciano , Kevin Kirby
发明人： Janis Brown , Ron Allred , Tom Duncan , Andrew Facciano , Kevin Kirby
IPC分类号： F42B15/34 , B32B18/00 , F42B12/76 , B64C1/10
CPC分类号： F42B12/76 , Y10T428/24942 , Y10T428/24994 , Y10T428/24995 , Y10T428/249952 , Y10T428/31525 , Y10T428/31529 , Y10T428/31663 , Y10T428/31678 , Y10T442/2795
摘要： A surface-protected composite article, such as a missile component, is prepared with a heat-sink substrate, a first composite layer of an pre-ceramic-matrix structural composite material, and a second composite layer of a reinforced silicone pre-ceramic material. The silicone material is co-curable with the organic matrix of the first composite layer. The silicone at the surface of the article is thereafter converted to a silica refractory by an appropriate treatment such as exposure to an oxygen-rich plasma or a high-surface temperature. The silica protects the surface of the composite material.
摘要翻译：用散热衬底，预陶瓷 - 基质结构复合材料的第一复合层和增强硅氧烷预陶瓷材料的第二复合层制备表面保护的复合制品，例如导弹组件。硅氧烷材料可与第一复合层的有机基质共固化。然后通过诸如暴露于富氧等离子体或高表面温度的适当处理将制品表面处的硅氧烷转化为二氧化硅耐火材料。二氧化硅保护复合材料的表面。

70. 发明授权

US5941479A Vehicle having a ceramic radome affixed thereto by a complaint metallic "T"-flexure element 失效
标题翻译：车辆具有通过投诉金属“T”弹性元件固定在其上的陶瓷天线罩
公开(公告)号：US5941479A
公开(公告)日：1999-08-24
申请号：US121134
申请日：1998-07-22
申请人： Wayne L. Sunne , Peter A. Nagy , Edward B. Liguori
发明人： Wayne L. Sunne , Peter A. Nagy , Edward B. Liguori
IPC分类号： B64C1/36 , B64C1/00 , B64C1/38 , F42B10/46 , H01Q1/28 , H01Q1/42 , B64C1/10
CPC分类号： H01Q1/42 , H01Q1/28
摘要： A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular "T"-flexure element is disposed structurally between the radome and the body and is integral with the body. A niobium-containing washer is disposed between the radome and the "T"-flexure element. The "T"-flexure element includes an elongated compliant arm region and a cross bar region positioned adjacent the radome such that the niobium-containing washer is situated between a lower margin surface of the radome and an upper side of the crossbar region. A first brazed butt joint is formed between the lower margin surface of the radome and an upper surface of the niobium-containing washer, while a second brazed butt joint is formed between a lower surface of the niobium-containing washer and the crossbar region of the "T"-flexure element. Two separate brazing materials are employed to be compatible with the respective materials (radome and niobium washer; niobium washer and "T"-flexure element), but have substantially the same brazing temperature to permit brazing the radome to the body in a single brazing operation.
摘要翻译：导弹具有其中具有大致圆形的鼻部开口的主体，以及尺寸适于覆盖鼻部开口的陶瓷天线罩。符合金属的圆形“T”弹簧元件结构地设置在天体罩和主体之间，并与身体成一体。含钕的洗涤器设置在天线罩和“T”型穿刺元件之间。 “T”弹簧元件包括细长的柔性臂区域和邻近天线罩定位的横杆区域，使得含铌垫圈位于天线罩的下边缘表面和横梁区域的上侧之间。第一钎焊对接接头形成在天线罩的下边缘表面和含铌垫圈的上表面之间，而第二钎焊对接接头形成在含铌垫圈的下表面和 “T”弹簧元件。使用两种单独的钎焊材料与各种材料（天线罩和铌垫圈;铌垫圈和“T” - 复合元件）相容，但是具有基本上相同的钎焊温度，以允许在单个钎焊操作中将天线罩钎焊到身体。

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