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 | ROTORCRAFT TOP FAIRING HAVING A PROFILE IN THE SHAPE OF A TRUNCATED DROP OF WATER THAT IS PROVIDED WITH A HUMP OF UNEVEN SURFACE | US14547586 | 2014-11-19 | US20150147177A1 | 2015-05-28 | David ALFANO |
| A rotorcraft provided on top with a fairing (3) arranged below the rotary wing of a main rotor of substantially vertical axis of the rotorcraft, and covering a mechanism enabling the blades of the rotary wing of the main rotor to be operated. The streamlined shape of the fairing (3) is shaped longitudinally like a drop of water that is truncated in its rear portion. The truncated portion (6) of the waterdrop-shaped profile of the fairing (3) forms the rear wall of the fairing (3) and is provided with a transversely middle hump (7). Said hump (7) is provided with projections in relief (9) arranged as waves in a longitudinal succession extending along the side walls of the fairing (3), and the truncated portion (6) is arranged in a plane sloping towards the rear of the rotorcraft. | ||||||
| 202 | COUNTER-ROTATING ROTOR SYSTEM WITH FAIRING | US14073301 | 2013-11-06 | US20150122941A1 | 2015-05-07 | Matthew Harrigan |
| A coaxial, dual rotor system for an aircraft includes a first rotor assembly located at a rotor axis and a second rotor assembly located at the rotor axis. An aerodynamic fairing is positioned between the first rotor assembly and the second rotor assembly along the rotor axis. A planetary gear arrangement is operably connected to the fairing and operably connected to an airframe of the aircraft to maintain a selected rotational orientation of the fairing about the rotor axis relative to the airframe. | ||||||
| 203 | Fresh air inlet for an aircraft | US12994911 | 2009-05-27 | US08973867B2 | 2015-03-10 | Johannes Eichholz; Jens Beier; Alexander Solntsev; Ruediger Schmidt |
| A fresh air inlet for an aircraft features a ram air inlet with a ram air inlet opening, a secondary air inlet opening separate from the ram air inlet and a movably mounted flap. The flap can be moved into a first or second position, and essentially covers the secondary air inlet opening in the first position and at least partially opens the secondary air inlet opening and extends away from the aircraft body in the second position to shield the ram air inlet opening from foreign matter in the air. The secondary air inlet reduces 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. The ram air inlet can be optimized for cruising phases, and the energy expenditure for any downstream compressors and flow-induced noises can be considerably reduced. | ||||||
| 204 | Supporting pillar for an aircraft's structural component manufactured by a selective laser melting process | US13061240 | 2009-07-30 | US08960605B2 | 2015-02-24 | 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. | ||||||
| 205 | Hinge sealing element and an assembly including said element | US12662955 | 2010-05-13 | US08919703B2 | 2014-12-30 | Simon John Parker |
| A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin. | ||||||
| 206 | Blade seal | US12780263 | 2010-05-14 | US08899528B2 | 2014-12-02 | Christopher Coconnier |
| A blade seal comprises a flexible member having a relatively thick edge opposite a relatively thin edge, and an actuator at least partially embedded in the flexible member for actively deflecting the thin edge with respect to the thick edge upon activation of the actuator. The blade seal may be fixed to an aerodynamic trailing edge of either a fixed aerofoil portion or a flight control surface of an aerofoil for sealing between the fixed aerofoil portion and the flight control surface. Also, a method of sealing an aerofoil using the blade seal. | ||||||
| 207 | Bridging seal | US13018537 | 2011-02-01 | US08876051B2 | 2014-11-04 | 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. | ||||||
| 208 | LOW DRAG ROTOR SYSTEM | US13856062 | 2013-04-03 | US20140299709A1 | 2014-10-09 | Frank P. D'Anna |
| A rotor assembly includes a rotor hub rotatable about a central axis including a plurality of rotor hub arms and blade yokes, each blade yoke including yoke arms located at opposing lateral sides of a corresponding one of the rotor hub arms to which the rotor hub arm is operably connected. The rotor assembly further includes blade retention bearings, each blade retention bearing being a single-element bearing disposed at a corresponding one of the rotor hub arms and which is supportive of a corresponding one of the blade yokes. Rotor blades are secured to corresponding ones of the blade yokes. | ||||||
| 209 | Thermal barrier coated RF radomes and method | US12629044 | 2009-12-01 | US08765230B1 | 2014-07-01 | John C. Waldrop, III; Daniel E. Driemeyer; Laura S. Riegel; Stanley A. Lawton |
| Thermal barrier coated RF radomes and a method for making the same are provided. In an embodiment of the disclosure, there is provided a method for making a thermal barrier coated radio frequency (RF) radome. The method comprises providing a radio frequency (RF) radome. The method further comprises applying a thermal barrier coating having a dielectric constant less than about 2.0 onto a surface of the radome to form a thermal barrier coated RF radome. The thermal barrier coating reduces a structure temperature of the radome by greater than 300 degrees Fahrenheit to enhance thermo-mechanical properties and performance of the RF radome. | ||||||
| 210 | Wing-to-body faring with spray-on foam and noise reduction method | US13741172 | 2013-01-14 | US08752783B2 | 2014-06-17 | John-Shyue Lin; Herbert L Hoffman; Hugh 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. | ||||||
| 211 | RETRACTABLE EQUIPMENT SYSTEM INCLUDING A DEVICE OPTIMIZED FOR DRIVING PROTECTION FLAPS | US14092194 | 2013-11-27 | US20140158824A1 | 2014-06-12 | Michel L'HERITIER; Eric DOUSTENS; Philippe BOSC; Philippe CASTAGNE |
| A system for retractable equipment is proposed that has movable protection flaps and in which a flap drive device serves to drive the flaps in optimized movement, while providing mechanical coupling between the flaps and the retractable equipment in such a manner that a common motor member can be used for driving both the equipment and the flaps. The drive device includes a cam secured to a frame of the system and a cam follower mechanically coupled to the retractable equipment and to a flap drive member. The path followed by the retractable equipment can thus also be optimized. | ||||||
| 212 | Formvariable Aerodynamic Fairing Body For A Flap Actuator Mechanism Of An Aircraft | US14089793 | 2013-11-26 | US20140151510A1 | 2014-06-05 | Karsten Schroeder; Hendrik Friedel |
| An aerodynamic fairing body for an aircraft, a corresponding aircraft and a corresponding method of manufacture for an aerodynamic fairing body are described. The fairing body is configured so as to accommodate a flap adjustment mechanism. Further, the fairing body is configured so as to be arranged at a predetermined distance from an engine of the aircraft, which produces a blast which varies depending on the flight phase. Furthermore, the fairing body is configured so as to be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently. In other words, the fairing body can be varied in shape in such a way that it is located outside the engine blast in any flight phase of the aircraft. | ||||||
| 213 | Flow channels | US13908522 | 2013-06-03 | US08740149B1 | 2014-06-03 | Gregory G. Thumann |
| The present disclosure relates to flow channels comprising a channel length having a first portion approximately parallel to the maximum waterline thickness location of a body and at least a second portion non-parallel thereto, a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of the surface of the body, and at least a portion of the free edge being arcuate. A method comprises providing the fluid channel attachable to a body, modifying resultant vortices and reducing or minimizing shock formations or separation regions of the freestream. | ||||||
| 214 | DOUBLE-CURVED COVER FOR COVERING A GAP BETWEEN TWO STRUCTURAL PORTIONS OF AN AIRCRAFT | US14126790 | 2011-06-16 | US20140131513A1 | 2014-05-15 | Jakob Bjerkemo |
| A cover for covering a gap between a first structural portion and a second structural portion of an aerial vehicle. A first attachment section is attachable to the first structural portion. A second flexible section covers the gap. The second flexible section includes an abutment portion for abutting against the second structural portion in an operating state. The abutment portion in an unloaded state forms an undulating shape having troughs and crests extending along a curved plane. The curvature of the curved plane essentially corresponds with the curvature of the surface of the second structural portion. The troughs are provided for engagement with the surface in the operating state such that the troughs tend to be flatten out and propagate over the surface pressing down neighboring crests towards the surface for providing a close fit between the cover and the second structural portion. | ||||||
| 215 | Aircraft with reduced environmental impact | US13973688 | 2013-08-22 | US08714475B2 | 2014-05-06 | Pierre-Emmanuel Gall; Guillaume Gallant |
| An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground. | ||||||
| 216 | Landing gear | US12855755 | 2010-08-13 | US08714473B2 | 2014-05-06 | 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. | ||||||
| 217 | WING-TO-BODY FARING WITH SPRAY-ON FOAM AND NOISE REDUCTION METHOD | US13741172 | 2013-01-14 | US20140027569A1 | 2014-01-30 | Juhn-Shyue Lin; Herbert L Hoffman; Hugh 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. | ||||||
| 218 | AIRCRAFT WITH REDUCED ENVIRONMENTAL IMPACT | US13973688 | 2013-08-22 | US20130334365A1 | 2013-12-19 | Pierre-Emmanuel Gall; Guillaume Gallant |
| An aircraft with reduced environmental impact includes two turboprop engines mounted on the back of the aircraft at the rear thereof, and one acoustic masking device per turboprop engine. The acoustic masking device includes a masking element, such as a flap, which can move between a position in which it is retracted into the wing, and a position in which it is extended toward the rear of the wing. In the extended position, the flap intercepts the noise area generated toward the front by the turboprop engine, so as to reduce the perception of noise on the ground. | ||||||
| 219 | System and method for affixing gateboxes to an aircraft | US13078286 | 2011-04-01 | US08579234B2 | 2013-11-12 | Larry D. Thompson |
| A system for affixing a gatebox to an aircraft includes a first type of gatebox operable to release material from an aircraft, a second type of gatebox operable to release material from the aircraft, a frame coupled to the aircraft operable to receive a selected one of the first type of gatebox and the second type of gatebox; and a plurality of fastenings operable to secure the selected one of the first type of gatebox and the second type of gatebox to the frame. | ||||||
| 220 | Helicopter rotor comprising a vibration damper, and method for updating the same | US12665303 | 2008-06-19 | US08573935B2 | 2013-11-05 | Santino Pancotti |
| A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades. | ||||||
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