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 |
|---|---|---|---|---|---|---|
| 241 | Fuel range for an aircraft | US11644854 | 2006-12-22 | US08172181B2 | 2012-05-08 | Calvin Burgess |
| An apparatus and method for improving the fuel range of an aircraft are provided. The aircraft includes a fuselage with a front windshield, and an external skin providing a top cover for a cockpit of the aircraft. The apparatus includes an aerodynamic fairing secured adjacent the windshield and enclosing the external skin covering the cockpit for a reduction in an abrupt change in area encountered by air flowing along the length of the fuselage. An enclosure is formed between the aerodynamic fairing and the external skin in which a fuel bladder, configured with a reticulated polyurethane foam insert, may be disposed for added fuel capacity of the aircraft. The method includes steps of providing an aerodynamic fairing configured to balance the flow of fluid over the aircraft during flight, and securing the aerodynamic fairing atop the aircraft and adjacent the front windshield. | ||||||
| 242 | WING-TO-BODY FAIRING WITH SPRAY-ON FOAM AND NOISE REDUCTION METHOD | US12850036 | 2010-08-04 | US20120032024A1 | 2012-02-09 | Juhn-Shyue Lin; Herbert L. Hoffman; Hugh W. Poling |
| A fairing includes a fairing body having a fairing interior and an interior surface and a spray-on insulation foam layer provided on the interior surface of the fairing body. | ||||||
| 243 | METHOD AND APPARATUS FOR CONTROLLING FLOW ABOUT A TURRET | US12842534 | 2010-07-23 | US20120018004A1 | 2012-01-26 | Alan Z. Ullman |
| Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret, such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be similarly reduced such that the performance of a system, such as a laser system, housed by the turret may be improved. To reduce flow separation, a motive flow may be provided by ejector nozzles that open through the surface and are positioned proximate to and aft of the turret relative to the ambient flow. The motive flow has a greater velocity than the ambient flow to thereby create a region aft of the turret of reduced pressure relative to an ambient pressure. Within this region of reduced pressure aft of the turret, a portion of the ambient flow mixes with the motive flow, thereby reducing or eliminating flow separation. | ||||||
| 244 | Method of reducing the compressibility drag of a wing, and container implementing the method | US12255296 | 2008-10-21 | US08100358B2 | 2012-01-24 | Thierry Fol; Cyril Bonnaud |
| The present invention provides a method of reducing the compressibility drag of wing, and it also provides a container implementing the method. The container (10, 10′, 10″) is provided successively with a front portion (11) in the vicinity of its leading edge (14), then with an intermediate portion (12), and then with a rear portion (13) in the vicinity of its trailing edge (15), said rear portion (13) tapering progressively in a direction going from the leading edge (14) of the container towards its trailing edge (15). Furthermore, said rear portion (13) is extended by connection means (17) enabling the container (10, 10′, 10″) to be connected under the wing (1) in such a manner that said tapering rear portion (13) is partially upstream from the leading edge (2) of the wing (1). | ||||||
| 245 | Methods and apparatus for optical propagation improvement system | US12359064 | 2009-01-23 | US08096507B2 | 2012-01-17 | Alan B. Cain; Eric J. Jumper; Donald J. Wittich, III; Edward J. Kerschen; David Cavalieri; T. Terry Ng |
| An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section. | ||||||
| 246 | PACKER ASSEMBLY | US13114077 | 2011-05-24 | US20110293362A1 | 2011-12-01 | Paul BLADES |
| An assembly comprising first and second structural components and a packer disposed between the first and second components, wherein the first component and the packer have mating part-spherical surfaces, and the first and second components are fixed relative to one another. Also, a method of aligning first and second structural components relative to one another to form an assembly, the method comprising bringing together first and second structural components with a packer disposed between the components, wherein the first component and the packer have mating part-spherical surfaces, sliding adjustment of the first component relative to the packer until the first and second components are aligned in a desired relationship, and then fixing the first and second components relative to one another. | ||||||
| 247 | Energy absorbing impact band | US12959222 | 2010-12-02 | US08066222B2 | 2011-11-29 | Timothy J. Lee; Jason L. Firko; Jonathan W. Gabrys |
| An energy absorbing system may include a structure formed of an inner face sheet and an outer face sheet and having a core positioned therebetween. The structure may have a leading edge. An impact member formed of a plastically deformable material may be positioned with the inner face sheet within an area of the leading edge. The impact member may absorb energy from an impact of a projectile with the leading edge and redistributing the energy of the impact to the structure. | ||||||
| 248 | SUPPORTING PILLAR FOR AN AIRCRAFT'S STRUCTURAL COMPONENT MANUFACTURED BY A SELECTIVE LASER MELTING PROCESS | US13061240 | 2009-07-30 | US20110253878A1 | 2011-10-20 | Christoph Klahn; Rüdy Gysemberg; Olaf Rehme |
| The invention relates to an elongated supporting pillar for a high-strength structural component, wherein the supporting pillar is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material. | ||||||
| 249 | METHOD FOR MANUFACTURING AND ATTACHMENT OF WING FAIRINGS | US13105572 | 2011-05-11 | US20110212310A1 | 2011-09-01 | Roy Anthony Eggink; David Scott Eberhardt |
| A method and apparatus for manufacturing and installing a fairing on an aircraft. In one advantageous embodiment, a composite fairing is installed on the aircraft. A composite sheet having a form of the composite fairing is formed. A plurality of cured composite tiles is created from the composite sheet, wherein spaces are present between the plurality of composite tiles. The plurality of composite tiles is cured to form the composite fairing. The composite fairing is attached to a surface of the aircraft. The spaces between the plurality of composite tiles are filled with a flexible filler. | ||||||
| 250 | AIRCRAFT FAIRING | US13127606 | 2008-11-05 | US20110204185A1 | 2011-08-25 | Neil John Lyons |
| A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing. | ||||||
| 251 | Method for manufacturing and attachment of wing fairings | US11861024 | 2007-09-25 | US07998392B2 | 2011-08-16 | Roy Anthony Eggink; David Scott Eberhardt |
| A method and apparatus for manufacturing and installing a fairing on an aircraft. In one advantageous embodiment, a composite fairing is installed on the aircraft. A composite sheet having a form of the composite fairing is formed. A plurality of cured composite tiles is created from the composite sheet, wherein spaces are present between the plurality of composite tiles. The plurality of composite tiles is cured to form the composite fairing. The composite fairing is attached to a surface of the aircraft. The spaces between the plurality of composite tiles are filled with a flexible filler. | ||||||
| 252 | BRIDGING SEAL | US13018537 | 2011-02-01 | US20110186690A1 | 2011-08-04 | David Mark STEWART |
| A bridging seal comprising a stack of two or more layers of elastomer, the bridging seal having a first edge and a second edge opposite the first edge, adjacent layers being attached to each other at the first and second edges, wherein adjacent layers of the bridging seal have opposing surfaces and a substantial portion of the opposing surfaces is unbonded. The bridging seal may be used to seal a gap between two aerodynamic surfaces on an aircraft. | ||||||
| 253 | SLOT SEAL | US12783642 | 2010-05-20 | US20110174933A1 | 2011-07-21 | Paul BLADES |
| A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door. | ||||||
| 254 | BLUFF BODY NOISE CONTROL | US12998115 | 2009-09-28 | US20110168483A1 | 2011-07-14 | Leung Choi Chow; David Angland; Xin Zhang; Michael Goodyer |
| The present invention provides a method of and apparatus for, reducing noise caused by the interaction of airflow between two bluff bodies which are in a generally tandem arrangement, the method comprising providing flow control such that the peak turbulence is at least partially displaced from, or reduced at, the surface of the downstream body. The invention also provides an aircraft noise reduction device, and a method of using such a device, comprising a flow control apparatus (2) arranged to be positioned downstream of a flow-facing element (1), wherein the flow control apparatus is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element, and wherein the flow control apparatus (2) is arranged to be moveable in relation to the flow-facing element (1) between a stowed position and a deployed position. | ||||||
| 255 | FRESH AIR INLET FOR AN AIRCRAFT | US12994911 | 2009-05-27 | US20110136425A1 | 2011-06-09 | Johannes Eichholz; Jens Beier; Alexander Solntsev; Ruediger Schmidt |
| The invention relates to a fresh air inlet for an aircraft that features at least one ram air inlet with at least one ram air inlet opening, at least one secondary air inlet opening that is spaced apart from the ram air inlet and at least one movably mounted flap, wherein the flap can be moved into a first position and into a second position, and wherein the flap essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and at least in certain areas extends into the air flow directed toward the ram air inlet opening in order to shield the ram air inlet opening from foreign matter in the second position. The air inlet according to the invention makes it possible to reduce the pressure loss of the air inlet on the ground or during flight phases with relatively slow speed due to the enlarged cross-sectional surface. This results in that the actual ram air inlet can be optimized for cruising phases, and that the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced. | ||||||
| 256 | Deflection device for a stream body | US11183475 | 2005-07-18 | US07931236B2 | 2011-04-26 | Damien Lejeau; Petra Aumann; Detlev Schwetzler |
| The present application describes to a deflection device, for example, for a blunt stream body. The deflection device has an edge, which, for example, can be mounted to the stream body. In an advantageous manner, the deflection device allows an influencing of the slipstream in such a way that turbulences, which are connected with the slipstream and form downstream of blunt stream bodies, have as little influence as possible on the dragged object in order to avoid the formation of building-up motions of the dragged object, which lead to instabilities. | ||||||
| 257 | Method and apparatus for enhancing engine-powered lift in an aircraft | US11927290 | 2007-10-29 | US07878458B2 | 2011-02-01 | Arvin Shmilovich; Yoram Yadlin; Robert D. Gregg, III; Roger W. Clark |
| Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft. | ||||||
| 258 | Landing Gear | US12855755 | 2010-08-13 | US20110001004A1 | 2011-01-06 | Christopher Neil Wood |
| An aircraft landing gear is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear, including inverting and fairing the nose-gear shock-absorbing leg, providing faired twin in-line oleos and providing fairings that produce shielding air curtains. | ||||||
| 259 | KIT FOR MODIFYING A STRUT OF AN AIRCRAFT WITH AN AERODYNAMIC COVER | US12813445 | 2010-06-10 | US20100320326A1 | 2010-12-23 | Garold Toews |
| A kit for modifying a strut of an aircraft with an aerodynamic cover includes a rigid sheath formed from a first portion and a second portion. Each of the first portion and the second portion have a curved shape. The rigid sheath includes an angled leading edge and an angled trailing edge. Convex surfaces connect the leading edge and the angled trailing edge. There is an attachment for attaching the rigid sheath to the strut, the attachment securing the sheath to the strut such that the strut is positioned at the camber of the rigid sheath. | ||||||
| 260 | AIRCRAFT WIRE FAIRING | US12793761 | 2010-06-04 | US20100308169A1 | 2010-12-09 | Jack BLANCHARD; Anthony BRYANT; Andrew GOLLIN |
| A fairing has a moulded body and an electrical wire embedded therein. The body may be constructed from a moulded plastics material or a composite material. | ||||||
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