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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
261	Aircraft monument integrated attachment device	US13851838	2013-03-27	US09599138B2	2017-03-21	Peter John Leslie Burd
An attachment device for an aircraft monument is disclosed having a pair of spaced apart parallel plates having vertical sides and a rounded upper surface defining an arch. A panel attaches the spaced apart parallel plates along an inner radius, and a pair of lugs including a vertical channel is disposed below the plates for receiving fasteners to connect the attachment device to a rail or planar surface.
262	Multi-Role Aircraft With Interchangeable Mission Modules	US15352465	2016-11-15	US20170066532A1	2017-03-09	Abe Karem
A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.
263	Digital flexural materials	US13961880	2013-08-07	US09566758B2	2017-02-14	Kenneth C. Cheung; Neil Adam Gershenfeld
Digital flexural materials are kits of discrete parts that can be assembled into a lattice structure to produce functionally useful assemblies. Digital flexural materials enable design of materials with many small and inexpensive flexures that combine in a lattice geometry that permits deformation without compromising the strength of the assembly. The number of types of parts in a kit is small compared to the total number of parts. A product constructed from digital flexural materials comprises a set of discrete units that are assembled into the structure according to a lattice geometry, with a majority of the units being reversibly connected to at least two other units in the set according to the lattice geometry, and wherein, in response to loading of the structure, a reversible deformation of at least part of the structure occurs. An automated process may be employed for constructing a product from digital flexural materials.
264	MONOLITHIC PRIMARY STRUCTURAL PART FOR AIRCRAFT AND PROCESSES FOR MANUFACTURING IT	US15224079	2016-07-29	US20170028652A1	2017-02-02	Carlos Garcia Nieto; Francisco Javier Honorato Ruiz
A monolithic primary structural part for an aircraft made of carbon fiber composite material and glass fiber composite material and covered completely by at least one glass fiber ply on an external face of the structural part which includes carbon fiber plies. A method to determine the glass fiber composite plies in a monolithic primary structural part for aircraft, which includes calculating a number of glass fiber plies using a Damage Tolerance criteria for sizing structural parts, in which a number of glass fiber plies replace carbon fiber plies.
265	MODULAR INTELLIGENT TRANSPORTATION SYSTEM	US15185926	2016-06-17	US20170025000A1	2017-01-26	Paul J. Lagassey
A modular intelligent transportation system, comprising an environmentally protected enclosure, a system communications bus, a processor module, communicating with said bus, having a image data input and an audio input, the processor module analyzing the image data and/or audio input for data patterns represented therein, having at least one available option slot, a power supply, and a communication link for external communications, in which at least one available option slot can be occupied by a wireless local area network access point, having a communications path between said communications link and said wireless access point, or other modular components.
266	Aircraft fuselage	US14154756	2014-01-14	US09533755B2	2017-01-03	William M. Otto
A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.
267	AIRCRAFT STRUCTURAL COMPONENT THAT IS ADAPTED FOR ABSORBING AND TRANSMITTING FORCES IN AN AIRCRAFT	US15176292	2016-06-08	US20160375979A1	2016-12-29	Kaspar VON-WILMOWSKY; Christian REICHENSPERGER; Andreas RACK
An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.
268	Aircraft fuselages	US14976988	2015-12-21	US09505481B2	2016-11-29	Bruce Raymond Detert
Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant.
269	PROCESS OR SYSTEM TO REDUCE COST AND WEIGHT OF AEROSPACE INTERIOR STRUCTURAL THERMOPLASTIC OR COMPOSITE PANEL CONSTRUCTIONS	US14708713	2015-05-11	US20160332412A1	2016-11-17	Kyle L. Gray; Nathanial C. Cuddy; Harold G. Erickson
Methods for manufacturing composite panels for use in the interior of an aircraft are disclosed, specifically, methods of manufacturing joggled composite panels comprising metal inserts and the resulting composite panels and inserts.
270	Water-tight compartment with removable hatch and two-sided gel seal for multiple conduit access	US14239749	2012-06-15	US09476251B2	2016-10-25	Ronald H. Olch; Pavel Belik
A water-tight or air-tight accessible compartment has a removable hatch sealed at the edge with elastically conformable opposing seals, with elongate communication elements extending into the compartment between the opposing seals, seals conforming to the topology formed between the compartment edge and the elongate communication elements.
271	Composite structure, aircraft wing and aircraft fuselage including composite structure, and method of manufacturing composite structure	US14373513	2013-02-14	US09475568B2	2016-10-25	Masahiro Kashiwagi; Yoshinori Nonaka; Toshio Abe
A composite structure (3) formed of a composite member which extends in one direction, includes holes (5), and is made of fiber reinforced plastics. A tensile load and/or a compressive load are applied to the composite structure (3) in the one direction. Tensile stiffness and/or compression stiffness of peripheral areas (3a) of the holes (5) is lower than tensile stiffness and/or compression stiffness of the other area (3b), which surrounds the peripheral areas (3a), in the one direction, and the width of the peripheral area (3a) in a direction orthogonal to the one direction is set to 1.1 times or less of the diameter of the hole (5) in the direction orthogonal to the one direction.
272	Composite filler	US14327600	2014-07-10	US09475256B2	2016-10-25	Charles William Thomas
A method and apparatus is presented. The composite filler comprises a number of layers of composite material and a core comprising a material which is non-bondable with the composite material.
273	Method for producing an aircraft structure component having an outer skin provided with electric conductor elements	US14016832	2013-09-03	US09462700B2	2016-10-04	Eckart Frankenberger
A method for producing an aircraft structure component is disclosed the component having an outer skin provided with electric conductor elements. The method includes providing an aircraft structure component having an outer skin, applying particles of electrically conductive material onto the outer surface of the outer skin of said aircraft structure component in a predetermined pattern, such that the accumulated particles of electrically conductive material form electric conductor elements along the outer surface of the outer skin, and applying particles of electrically insulating material onto the outer surface of the outer skin of said aircraft structure component in a predetermined pattern, such that the accumulated particles of electrically isolating material form an insulating layer for the electric conductor elements.
274	Aircraft having split level cabin floors	US12716606	2010-03-03	US09452817B1	2016-09-27	Mithra M. K. V. Sankrithi
An aircraft for carrying passengers and/or cargo has first, second and third cabins arranged in a split level floor configuration within a fuselage. The cabin floors are connected by stairs, elevators or escalators. Two of the cabins are stacked above a reduced height lower hold which acts as an energy absorbing crush zone in the event of a crash.
275	Safety device for a lithium electrochemical generator battery	US13839421	2013-03-15	US09412985B2	2016-08-09	Benoit Turbe; Jerome Calmejane; Benoit Vasselin; Philippe Genin
A safety device (1) for a lithium electrochemical generator battery, including a box (100), configured to house a plurality of lithium electrochemical generators; a cover (200) arranged gas-tightly on the opening (130) of the box; an opening (120) forming a vent situated in one of the walls of the box (100) or situated in the cover (200); a conduit (300) having two openings (311, 312) where one of the openings (311) is gas-tightly connected to the opening (120) forming a vent of the box; a covering part (400) positioned gas-tightly at an opening of a wall of the compartment and the second opening (312) of the conduit, and where said covering part comprises a portion (410) adapted to tear at a threshold pressure Ps; where the walls of the box, the cover, the conduit and the covering part are secured to each other so as to ensure sealing against the gases up to a pressure above the threshold pressure Ps.
276	Decompression unit	US13880201	2011-10-13	US09387917B2	2016-07-12	Erich Pamminger; Bernhard Kammerer
A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure Δp in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded.
277	GRAPHENE AEROSPACE COMPOSITES	US14589085	2015-01-05	US20160193809A1	2016-07-07	Keith Daniel Humfeld
Composite prepreg materials made from a plurality of layers of graphene film having a size that spans an entire width and an entire length of the composite prepreg material, each of the layers of graphene film being functionalized with holes formed through the graphene film, amine groups formed on both an upper and a lower surface of the graphene film, epoxide groups formed on at least one edge of the graphene film, amine monomers and/or epoxy monomers. The plurality of layers may be formed by stacking a plurality of layers of graphene film to form a stacked composite prepreg material or by folding a graphene film to form a crumpled composite prepreg material.
278	SANDWICH PANEL AND METHOD TO FORM THE PANEL	US14969946	2015-12-15	US20160167763A1	2016-06-16	David BRAKES
A composite panel including first and second parallel planar face sheets and a core sandwiched between the first and second face sheets. The core includes a regular array of solid elements bonded to the first and second face sheets. Also, a method of manufacturing the composite panel.
279	Variation compensating assembly	US13746053	2013-01-21	US09365278B2	2016-06-14	Ross Mitchell Blanton; Tracy L. Bagwill
An apparatus comprising an outer sleeve and an inner sleeve. The outer sleeve has a first channel with an inner wall with a first number of substantially planar surfaces. The inner sleeve has a second channel and an outer wall with a second number of substantially planar surfaces. The outer wall is configured to be received within the first channel. At least one of the second number of substantially planar surfaces on the outer wall of the inner sleeve is configured to slide against at least one of the first number of substantially planar surfaces.
280	Apparatus for attachment of wing panels	US13688475	2012-11-29	US09334038B2	2016-05-10	David Mark Stewart
A shroud panel (60) is attached to a wing skin overhang (28) by a series of pivoting butt straps (86) to permit relative strains to occur.

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