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61. 发明授权

US08015973B2 System and method for aircraft cabin atmospheric composition control 失效
标题翻译：飞机机舱大气成分控制系统与方法
公开(公告)号：US08015973B2
公开(公告)日：2011-09-13
申请号：US10708217
申请日：2004-02-17
申请人： Robert Geary
发明人： Robert Geary
IPC分类号： B64D45/00 , B64D11/00 , B64D13/02 , B64C1/10 , B64G1/52 , A61M16/00 , F25J3/00 , B63J2/00 , B60H1/00
CPC分类号： B64D13/06 , B64D2013/0681
摘要： Method and arrangement for adjusting nitrogen and oxygen concentrations within regions of an aircraft. The method includes separating nitrogen from ambient air onboard an aircraft thereby establishing a high-concentration nitrogen supply and then dispensing high-concentration nitrogen from the supply to a fire-susceptible, non-habitable region of the aircraft where the high-concentration nitrogen is reservoired thereby decreasing the capability for the atmosphere therein to support combustion. Oxygen is also separated from the ambient air thereby establishing a high-concentration oxygen supply that is dispensed to an occupant cabin of the aircraft thereby increasing the level of oxygen concentration within the cabin to a level greater than the naturally occurring concentration of oxygen at the experienced internal cabin pressure. When it is determined that reduced oxygen concentration is required in the occupant cabin, the reservoired high-concentration nitrogen is moved into the passenger cabin diluting the oxygen-elevated environment.
摘要翻译：调整飞机区域内氮和氧浓度的方法和装置。该方法包括从飞机上的环境空气中分离氮气，从而建立高浓度氮气供应，然后将高浓度氮气从供应部分分配到高浓度氮气储存的飞机的易燃，不可居住区域从而降低其中的气氛的能力以支持燃烧。氧气也与环境空气分离，从而建立高浓度氧气供应，其被分配到飞行器的乘客舱，从而将舱室内的氧浓度水平提高到大于经验的氧气的天然浓度内部舱内压力。当确定在乘员舱中需要降低的氧浓度时，将储存的高浓度氮气移动到乘客舱中，以稀释氧气升高的环境。

62. 发明申请

US20110139931A1 FIREPROOF BIDIRECTIONAL DECOMPRESSION PANEL 有权
标题翻译： FIREPROOF双向解码面板
公开(公告)号：US20110139931A1
公开(公告)日：2011-06-16
申请号：US12637721
申请日：2009-12-14
申请人： Fred W. Opp , Keith A. Krueger
发明人： Fred W. Opp , Keith A. Krueger
IPC分类号： B64C1/10 , B64D45/00
CPC分类号： B64C1/18 , B64C2001/009
摘要： 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.
摘要翻译：防火双向减压面板包括框架构件和压力释放面板构件，其可释放地保持在框架构件上，以可移除地覆盖飞机隔板（例如飞机货舱的侧壁）的减压通风口。在减压事件期间，当隔着隔板存在预定的压力差时，压力释放板构件在从框架构件的两个相反方向中的任一方向上被双向释放。减压面板组件是耐火的，并且与现有的常规减压面板组件相比，重量减轻，部件减少。

63. 发明授权

US07943227B2 Ceramic heat shield 有权
标题翻译：陶瓷隔热罩
公开(公告)号：US07943227B2
公开(公告)日：2011-05-17
申请号：US11870513
申请日：2007-10-11
申请人： Thomas J. Connelly
发明人： Thomas J. Connelly
IPC分类号： B23B3/00 , B23B23/02 , B64C1/10 , B64D7/00 , B64G1/52
CPC分类号： B64D33/04 , B64D29/02 , B64G1/58 , Y10T428/24008 , Y10T428/24479 , Y10T428/24488 , Y10T428/24562 , Y10T428/24612 , Y10T428/24777
摘要： A heat shield includes a ceramic composite heat shield panel having a generally concave first surface and a generally convex second surface and a pair of thickened panel edge portions provided in the heat shield panel. A heat shield assembly is also disclosed.
摘要翻译：隔热罩包括具有大致凹入的第一表面和大致凸形的第二表面的陶瓷复合隔热板和设置在隔热板中的一对增厚板边缘部分。还公开了一种隔热罩组件。

64. 发明授权

US07927686B2 Composite heat shield 有权
标题翻译：复合隔热罩
公开(公告)号：US07927686B2
公开(公告)日：2011-04-19
申请号：US12170789
申请日：2008-07-10
申请人： Edward Zielinski , Thomas J. Connelly
发明人： Edward Zielinski , Thomas J. Connelly
IPC分类号： B32B3/00 , B32B3/12 , B64C1/10 , B64C1/00 , B64D7/00
CPC分类号： B64D33/04 , B64C7/02 , B64D29/02 , B64G1/58 , Y10T428/1314 , Y10T428/1317 , Y10T428/234 , Y10T428/24562 , Y10T428/24661
摘要： A composite heat shield includes a ceramic composite heat shield body comprising a pair of generally spaced-apart heat shield side panels, a heat shield bottom panel extending between the heat shield side panels and having a heat exposure surface, a heat shield top panel extending between the heat shield side panels in spaced-apart relationship with respect to the heat shield bottom panel and having at least one heat shield surface and at least one heat shield cavity defined between the heat shield bottom panel and the heat shield top panel.
摘要翻译：复合隔热罩包括陶瓷复合隔热罩体，该陶瓷复合隔热罩主体包括一对大致隔开的隔热屏侧板，在隔热屏侧面板之间延伸并具有热曝露表面的隔热罩底板，所述隔热罩侧板相对于所述隔热罩底板间隔开，并且具有至少一个隔热表面和限定在所述隔热罩底板和所述隔热罩顶板之间的至少一个隔热罩。

65. 发明申请

US20110024563A1 PRESSURE FUSELAGE OF AN AIRCRAFT OR SPACECRAFT WITH PRESSURE CALOTTE 失效
标题翻译：使用压力计的飞机压缩机或压缩机的压力
公开(公告)号：US20110024563A1
公开(公告)日：2011-02-03
申请号：US12845012
申请日：2010-07-28
申请人： Richard BAUER , Pierre ZAHLEN
发明人： Richard BAUER , Pierre ZAHLEN
IPC分类号： B64C1/10
CPC分类号： B64C1/10
摘要： A pressure fuselage of an aircraft or a spacecraft includes at least two fuselage sections disposed longitudinally along the fuselage; at least one pressure calotte disposed in the fuselage so as to form a pressurized area; and an arcuate frame profile having a Y-shaped cross-section with a long profile leg connected to at least one of the at least two fuselage sections and a short profile leg extending at an acute angle from the long profile leg toward an inside of the at least two fuselage sections and attached to the at least one pressure calotte.
摘要翻译：飞机或航天器的压力机身包括至少两个沿机身纵向设置的机身部分; 设置在机身中的至少一个压力杯，以形成加压区域; 以及弓形框架轮廓，其具有Y形横截面，其具有连接到所述至少两个机身部分中的至少一个的长型腿，以及从所述长型腿朝向所述长型轮的内侧以锐角延伸的短型腿至少两个机身部分并连接到所述至少一个压力辊。

66. 发明授权

US07736719B2 Protection panel for aircrafts 失效
标题翻译：飞机保护板
公开(公告)号：US07736719B2
公开(公告)日：2010-06-15
申请号：US12001148
申请日：2007-12-10
申请人： Giuliano Cattaneo , Luca Bottero
发明人： Giuliano Cattaneo , Luca Bottero
IPC分类号： B32B3/00 , B32B3/14 , B32B3/16 , B32B23/02 , B64C1/10 , B64D7/00
CPC分类号： B64D29/00 , F01D21/045 , F41H5/0485 , Y02T50/672 , Y10T428/195 , Y10T428/24488 , Y10T428/24612 , Y10T428/24777 , Y10T428/249921 , Y10T428/2848
摘要： Protection panel (3) for an aircraft suitable for being associated with at least a portion of the surface to be protected, consisting of a plurality of layers associated with each other made of aramid fibre in which at least one of said layers consists of an aramid fibre or unidirectional fabric.
摘要翻译：用于适用于与要保护的表面的至少一部分相关联的飞机的保护面板（3），其由彼此由芳族聚酰胺纤维相关联的多个层组成，其中所述层中的至少一个由芳族聚酰胺纤维或单向织物。

67. 发明授权

US07618005B1 Stealth bomber, transporter, air-to-air fueling tanker, and space plane 失效
标题翻译：隐形轰炸机，运输机，空对空加油车和太空飞机
公开(公告)号：US07618005B1
公开(公告)日：2009-11-17
申请号：US11789718
申请日：2007-04-25
申请人： Samuel Barran Tafoya
发明人： Samuel Barran Tafoya
IPC分类号： B64C1/10
CPC分类号： B64C1/064 , B64C1/065 , B64C2039/105 , Y02T50/12
摘要： A stealth transporter aircraft having a rhomboid airframe with a dihedral bottom surface and a top surface designed as an airfoil. The rhomboid cross-sectional configuration of the airframe gives it increased lift, stealth characteristics, and enhanced load bearing capacity. The aircraft does not have conventional wing structure and its dihedral bottom surface allows it to make wheels-up emergency landings on water and hard runway surfaces with greater pilot survivability. A rigid central tubular area extending nearly the full length of the airframe is configured for passengers, luggage, munitions, and/or equipment and provides a backbone for the aircraft. The aircraft further has rear engines, a large fuel carrying capability, and may also undergo primarily interior modifications for function as a space plane or air-to-air fueling tanker. A vortex spoiler on the side edges of the airframe is also preferred, which eliminates trails while in high altitude flight.
摘要翻译：隐形运输机具有具有二面底面的菱形机身和设计为翼型的顶面。机身的菱形横截面结构提高了提升，隐形特性和增强的承载能力。飞机没有传统的机翼结构，其二面底面允许其在水和硬的跑道表面上轮起紧急着陆，具有更大的飞行员生存能力。延伸几乎整个机身长度的刚性中央管状区域被配置为乘客，行李箱，弹药和/或设备，并为飞行器提供骨干。飞机还具有后发动机，具有大的燃料承载能力，并且还可以主要进行内部修改以用作空间飞机或空对空加油车。在机身侧边缘的涡流扰流器也是优选的，这在高空飞行中消除了小径。

68. 发明申请

US20090121081A1 Composite Bulkhead and Skin Construction 有权
标题翻译：复合隔板和皮肤结构
公开(公告)号：US20090121081A1
公开(公告)日：2009-05-14
申请号：US12246904
申请日：2008-10-07
申请人： Abe Karem
发明人： Abe Karem
IPC分类号： B64C1/10
CPC分类号： B64C1/10 , B64C2001/0072 , Y02T50/43
摘要： Aircraft fuselage structures have fuselage bulkheads in which the bulkhead outer caps are integrated with the skin, thereby reducing fastener count and weight. These outer caps and skin are preferably co-cured to form a strong structure. The outer caps can be advantageously constructed as continuous hoops of pultruded elements. The outer cap need not be interrupted by contours or cutouts for stringers, saving weight and reducing complexity. It is contemplated that by integrating the bulkhead outer caps into the skin, a bulkhead can still maintain equivalent stiffness and strength, while saving a significant number of rivets as compared to a comparable design without the outer cap.
摘要翻译：飞机机身结构具有机身舱壁，其中隔板外盖与皮肤结合在一起，从而减少紧固件数量和重量。这些外盖和皮肤优选共固化以形成强结构。外盖可以有利地构造成拉挤元件的连续箍。外盖不需要被桁条的轮廓或切口中断，从而节省重量并降低复杂性。预期通过将隔板外盖整合到皮肤中，与没有外盖的可比设计相比，隔板仍能保持相当的刚度和强度，同时节省大量的铆钉。

69. 发明授权

US07516919B2 Aircraft archway architecture 有权
标题翻译：飞机拱门架构
公开(公告)号：US07516919B2
公开(公告)日：2009-04-14
申请号：US11865644
申请日：2007-10-01
申请人： David A. Young , Richard Fraker , R. Klaus Brauer , Peter S. Guard
发明人： David A. Young , Richard Fraker , R. Klaus Brauer , Peter S. Guard
IPC分类号： B64C1/10
CPC分类号： B64D11/00 , B64C1/066 , B64D11/0023 , B64D11/02 , B64D11/0691 , B64D2011/0046
摘要： An architectural archway for an aircraft. The archways can be positioned individually, or in pairs or other sets along the length of an aircraft fuselage. The archways are used to run or connect various transport elements, such as electrical wiring, water lines, and environmental control system conduits, between the upper crown, lower bay and passenger cabin of the aircraft. The invention simplifies installation complexity and eliminates the installation and variability associated with running transport elements between the various sections of the aircraft.
摘要翻译：一架飞机的建筑拱门。拱门可以沿飞机机身的长度单独定位或成对安装。拱门用于在飞机的上冠，下托架和客舱之间运行或连接各种运输元件，例如电线，水线和环境控制系统导管。本发明简化了安装复杂性，并消除了与飞机各部分之间的运输元件运行相关联的安装和变化。

70. 发明申请

US20070200030A1 Aircraft baffle seal 审中-公开
标题翻译：飞机挡板密封
公开(公告)号：US20070200030A1
公开(公告)日：2007-08-30
申请号：US11361734
申请日：2006-02-24
申请人： Daniel McFarlane , David McFarlane
发明人： Daniel McFarlane , David McFarlane
IPC分类号： B64C1/10
CPC分类号： B64D33/08 , B32B25/02 , B32B25/08 , B32B25/10 , B32B25/20 , B32B27/02 , B32B27/06 , B32B27/10 , B32B27/322 , B32B2262/0261 , B32B2262/0269 , B32B2262/101 , B32B2274/00 , B32B2307/746 , B32B2581/00 , B32B2605/18
摘要： Baffle seals having low coefficients of friction and materials for constructing such baffle seals are disclosed herein. A baffle seal of one embodiment comprises a sheet of material sized to seal a gap between an aircraft's baffle and cowl. The sheet of material has a contact side for contacting a cowl contact surface, and the contact side has a kinetic coefficient of friction that is not more than 0.4. In an embodiment, a sheet of material for forming an aircraft baffle seal is provided. The sheet includes a flexible primary layer and a flexible contact layer presenting a contact side. The contact side has a kinetic coefficient of friction that is not more than 0.4.
摘要翻译：本文公开了具有低摩擦系数的挡板密封件和用于构造这种挡板密封件的材料。一个实施例的挡板密封件包括尺寸适于密封飞机的挡板和整流罩之间的间隙的材料片。该片材具有用于接触整流罩接触表面的接触侧，并且接触侧具有不大于0.4的动摩擦系数。在一个实施例中，提供了一种用于形成飞机挡板密封件的材料片。片材包括柔性主层和呈现接触侧的柔性接触层。接触侧的动摩擦系数不大于0.4。

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