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 |
|---|---|---|---|---|---|---|
| 201 | Color applications for aerodynamic microstructures | US14705564 | 2015-05-06 | US09714083B2 | 2017-07-25 | Diane C. Rawlings |
| Color applications for aerodynamic microstructures are disclosed herein. One disclosed example apparatus includes an aerodynamic microstructure of a vehicle, sub-microstructures superimposed on the aerodynamic microstructure, and a color application defined on or within the microstructure. | ||||||
| 202 | A ROTORCRAFT TAIL BOOM, AND A ROTORCRAFT | US15318536 | 2015-06-04 | US20170121010A1 | 2017-05-04 | Debbie LEUSINK; David ALFANO |
| A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (Hext) and it extends laterally over an extension thickness (EPext), the extension height (Hext) lying in the range 0.05 times the maximum thickness (EPmax) of the structure, included, to 0.5 times the maximum thickness (EPmax), included, of the section, the extension thickness (EPext) lying in the range 0 to 0.4 times the maximum thickness (EPmax), included, of the section. | ||||||
| 203 | WING AERIAL REFUELING SYSTEM | US14256935 | 2014-04-19 | US20160144950A1 | 2016-05-26 | Stanley D. Ferguson; Ian J. Fialho; Richard C. Potter |
| An aircraft comprises a wing assembly, a pod, and a pylon attaching the pod to the wing assembly. The pylon has a swept pylon flap, which is configured to unload the pylon and pod during flight of the aircraft, and also to create downward flow that counters a vortex trailing the pod. | ||||||
| 204 | Wing structure and fairing device | US13499970 | 2010-10-07 | US09090346B2 | 2015-07-28 | Yukihide Kimura; Tomoaki Morimoto |
| A wing structure includes: a main wing that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing that is disposed so as to be separated from the main wing and faces the main wing at the front part side of the main wing, wherein a wing chord length of the auxiliary wing is shorter than a wing chord length of the main wing. A fluid contacts the auxiliary wing which is formed at the front part side of the main wing, the fluid is guided between the auxiliary wing and the main wing, and the fluid is compressed when passing between the auxiliary wing and the main wing, thereby appropriately forming a fluid compression process region on the surface of the main wing and increasing an acting force. | ||||||
| 205 | Wing for generating lift from an incident flow | US13640976 | 2011-04-14 | US08973874B2 | 2015-03-10 | Robert Jan Musters |
| The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge. | ||||||
| 206 | ATTACHMENT PYLON FOR AN UNDUCTED FAN | US14364981 | 2012-12-12 | US20140374566A1 | 2014-12-25 | Rasika Fernando; Nicolas Mehier; Fabien Monti; Nicolas Sirvin |
| A pylon configured to secure a turbine engine to a structural element of an aircraft, the pylon including a streamlined profile defined by two opposite faces and extending longitudinally between a leading edge and a trailing edge, and at least a first one of the two faces presenting at least locally a succession of non-through hollows and of bumps. | ||||||
| 207 | Landing gear assembly | US10552097 | 2004-04-07 | US08882043B2 | 2014-11-11 | Leung Choi Chow; Christopher Neil Wood |
| An aircraft landing gear (9) includes a wheel (1) having a wheel rim (3) on which a tire (4) is held. The gap (6) between the rim (3) and tire (4) is bridged and covered by a sealing element (7), which thereby presents a smooth surface to the air flowing over the wheel during flight of the aircraft (8). Thus, noise that would otherwise be generated by the interaction of air and the parts of the wheel (1) and/or tire (4) defining the gap (6) is reduced. Such noise reduction benefits may also be achieved by providing a tire (4) and wheel (1) so shaped that there is no gap (6) between the tire (4) and wheel rim (3). | ||||||
| 208 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176843 | 2014-02-10 | US20140224925A1 | 2014-08-14 | Donald Freund |
| Methods and systems for controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds are disclosed herein. The method includes, but is not limited to, monitoring, with a processor, a weight of the supersonic aircraft and a distribution of fuel onboard the supersonic aircraft. The method further includes, but is not limited to, determining, with the processor, that there is a deviation of the weight of the supersonic aircraft from a design-condition weight. The method still further includes, but is not limited to, controlling, with the processor, a redistribution of the fuel onboard the supersonic aircraft to adjust an amount of fuel stored within a wing to minimize a twist in the wing caused by the deviation. Such redistribution will reduce the magnitude of the sonic boom caused by the deviation. | ||||||
| 209 | SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM | US14176821 | 2014-02-10 | US20140224924A1 | 2014-08-14 | Donald Freund |
| A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist. | ||||||
| 210 | VARIABLE-WIDTH AERODYNAMIC DEVICE | US14136350 | 2013-12-20 | US20140217236A1 | 2014-08-07 | André dos Santos BONATTO; Francisco Keller KLUB; Julio Ramano MENEGHINI; Leandro Guilherme Crenite SIMÕES; Miacel Gianini Valle DO CARMO; Rafeal dos Snatos GIORIA; Stergios Pericles TSILOUFAS |
| There is described a variable-width aerodynamic device (10) associable to aerodynamic high lift structures (30), the variable-width aerodynamic device (10) comprising: a main body (11) substantially flat and having constant thickness; a first longitudinal edge (12) associated to the aerodynamic high lift structure (30); and a second non-rectilinear longitudinal edge (13), forming, with the first longitudinal edge (12), a variable width (Lv) along its length. | ||||||
| 211 | Ejector driven flow control for reducing velocity deficit profile downstream of an aerodynamic body | US12723678 | 2010-03-14 | US08690106B1 | 2014-04-08 | Mark A. Reissig |
| A system and method for reducing a velocity deficit from an aerodynamic body is disclosed. An air jet is injected into an ejector mixing chamber in the aerodynamic body. The air jet creates a suction effect in the ejector mixing chamber, which suctions boundary layer air from a perforated surface in at least one side of the aerodynamic body into a plenum chamber and into the ejector mixing chamber. The air jet ejects the boundary layer air and the air jet from a trailing edge slot of the ejector mixing chamber. Suctioning the boundary layer air and ejecting the boundary layer air and the air jet from the trailing edge slot reduces a velocity deficit on a trailing edge of the aerodynamic body. The reduced velocity deficit and the suctioning of boundary layer air reduce noise, turbulence, blade stress, and blade deformation. | ||||||
| 212 | CROSS-FLOW FAN, MOLDING DIE, AND FLUID FEEDER | US14002212 | 2012-02-28 | US20130336793A1 | 2013-12-19 | Yukishige Shiraichi; Masaki Ohtsuka |
| A cross-flow fan includes a plurality of fan blades provided to be circumferentially spaced apart from each other. The fan blade has an inner edge portion arranged on the radially inner side to/from which air flows in/out, and an outer edge portion arranged on the radially outer side to/from which air flows in/out. Fan blade has a blade surface extending between the inner edge portion and the outer edge portion. The blade surface includes a pressure surface arranged on the rotation direction side of the cross-flow fan and a suction surface arranged on the back side of the pressure surface. When cut along a plane orthogonal to the rotation axis of the cross-flow fan, the fan blade has a blade cross-sectional shape in which a concave portion concave from the pressure surface is formed. | ||||||
| 213 | LANDING GEAR FOR AN AIRCRAFT | US13902010 | 2013-05-24 | US20130313360A1 | 2013-11-28 | Leung Choi CHOW; Christopher Neil Wood; Philip Ian Campbell |
| The invention provides a landing gear 120 for an aircraft 110, the landing gear comprising a main strut 121 having a first upper end arranged to be moveably mounted to a structure of the aircraft, a landing gear wheel assembly 131, 132 connected to a second lower end of the main strut, the landing gear wheel assembly comprising at least one landing gear wheel arranged to roll in a fore-aft direction with respect to the main strut, and a stay 122 having a first upper end arranged to be connected to a structure of the aircraft, and a second lower end pivotally mounted to a mounting element 140 on the main strut, wherein the mounting element on the main strut is positioned substantially in line with the main strut in the fore-aft direction. The invention also provides a main strut, an aircraft and a kit of parts. | ||||||
| 214 | PLASMA-ENHANCED ACTIVE LAMINAR FLOW ACTUATOR SYSTEM | US13821196 | 2010-09-15 | US20130291979A1 | 2013-11-07 | Pontus Nordin; Göte Strindberg |
| The invention regards a plasma-enhanced active laminar flow actuator system (1) adapted to an aerodynamic surface (3) which has a nano-engineered composite material layer(5) comprising a set of electrodes arranged (7′, 7″) in at least an upper (P1) and a lower (P2) plane extending parallel with the aerodynamic surface (3); the electrodes (7′, 7″) comprising nano filaments (9); the electrodes (7′) of the upper plane (P1) are arranged in the aerodynamic surface (3) such that they define a smooth and hard aerodynamic surface (3);conductors (11, 11′) of nano filaments (9″) arranged for electrical communication between a control unit (13) and each of the electrodes (7′, 7″), wherein the control unit (13) is adapted to address current between cooperating electrodes (7′, 7″) of the upper and lower plane (P1, P2) from a current supply depending upon air flow characteristic signals fed from air flow sensor means (19). | ||||||
| 215 | INTERFACE ARRANGEMENT FOR AIRCRAFT LIFTING SURFACE | US13829629 | 2013-03-14 | US20130270392A1 | 2013-10-17 | FERNANDO MAESTRE DERQUI; IGNACIO OUTON HERNÁNDEZ |
| Interface arrangement for aircraft lifting surface between a first component and a second component made of composite materials and having an aerodynamic contour, wherein the first component comprises a primary joggled area and the second component comprises a secondary joggled area, such that the first component is joined to the second component by means of a supplementary part which accommodates in the primary joggled area and in the secondary joggled area, the secondary part being designed to maintain continuity of aerodynamic contour at the interface arrangement and to fill the gap between the first component and the second component, so the maximum thickness of the supplementary part being the depth of the primary joggled area, the depth of the primary joggled area being lower than the depth needed to accommodate the second component on the first component. | ||||||
| 216 | System for remote monitoring of aerodynamic flow conditions | US12898769 | 2010-10-06 | US08516899B2 | 2013-08-27 | John M. Obrecht |
| A system (1) for monitoring aerodynamic flow conditions over an aerodynamic member is provided. The system (1) includes a cantilevered arm (16) having a first conductive lead (18) configured for movement relative to a second conductive lead (20) for selective contact therewith in alternative response to a presence or absence of a turbulent air (22) flow thereover. In addition, the system (1) includes a circuit (24) comprising the first conductive lead (18) and the second conductive lead (20). A continuity condition in the circuit (24) between the first conductive lead (18) and the second conductive lead (20) is indicative of the presence or absence of the turbulent air flow (22). | ||||||
| 217 | BLUFF BODY NOISE CONTROL | US13680598 | 2012-11-19 | US20130193268A1 | 2013-08-01 | Leung Choi CHOW; Matthew SPITERI; Xin ZHANG; David ANGLAND; Michael GOODYER |
| An aircraft noise-reduction apparatus comprise a flow-facing element (1) and a flow control device (2) positioned downstream of the flow-facing element (1). The flow control device (2) is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element (1). | ||||||
| 218 | Nacelle assembly having inlet airfoil for a gas turbine engine | US11739216 | 2007-04-24 | US08408491B2 | 2013-04-02 | Ashok K. Jain; Michael Winter |
| A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly. | ||||||
| 219 | WING STRUCTURE AND FAIRING DEVICE | US13499970 | 2010-10-07 | US20120207609A1 | 2012-08-16 | Yukihide Kimura; Tomoaki Morimoto |
| A wing structure includes: a main wing that extends in a second direction intersecting a first direction as a fluid flow direction; and an auxiliary wing that is disposed so as to be separated from the main wing and faces the main wing at the front part side of the main wing, wherein a wing chord length of the auxiliary wing is shorter than a wing chord length of the main wing. A fluid contacts the auxiliary wing which is formed at the front part side of the main wing, the fluid is guided between the auxiliary wing and the main wing, and the fluid is compressed when passing between the auxiliary wing and the main wing, thereby appropriately forming a fluid compression process region on the surface of the main wing and increasing an acting force. | ||||||
| 220 | SYSTEM FOR REMOTE MONITORING OF AERODYNAMIC FLOW CONDITIONS | US12898769 | 2010-10-06 | US20120086209A1 | 2012-04-12 | John M. Obrecht |
| A system (1) for monitoring aerodynamic flow conditions over an aerodynamic member is provided. The system (1) includes a cantilevered arm (16) having a first conductive lead (18) configured for movement relative to a second conductive lead (20) for selective contact therewith in alternative response to a presence or absence of a turbulent air (22) flow thereover. In addition, the system (1) includes a circuit (24) comprising the first conductive lead (18) and the second conductive lead (20). A continuity condition in the circuit (24) between the first conductive lead (18) and the second conductive lead (20) is indicative of the presence or absence of the turbulent air flow (22). | ||||||
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