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 |
|---|---|---|---|---|---|---|
| 261 | BLADE SEAL | US12780263 | 2010-05-14 | US20100288888A1 | 2010-11-18 | 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. | ||||||
| 262 | Hinge sealing element and an assembly including said element | US12662955 | 2010-05-13 | US20100288887A1 | 2010-11-18 | 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. | ||||||
| 263 | PLANETARY DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM | US12810186 | 2008-01-02 | US20100270423A1 | 2010-10-28 | Timothy Fred Lauder |
| A de-rotation system includes a planetary gear set, and a fairing support structure mounted for rotation with a first ring gear. | ||||||
| 264 | Drag reduction fairing | US11230177 | 2005-09-19 | US07784737B2 | 2010-08-31 | Robert Michael Lee; Brian G. Evans |
| A vehicle including a body having an exterior surface and a protrusion extending outward from the surface. The vehicle further includes a fairing mounted on the surface directly adjacent and behind the protrusion. The fairing has a forward end, an aft end opposite the forward end, and opposing sides extending between the forward end and the aft end. The opposing sides become progressively closer together from the forward end to the aft end so that the bracket has a tapered shape. | ||||||
| 265 | CENTRAL SECTION OF AIRCRAFT WITH VENTRAL OR BELLY FAIRING CAPABLE OF MOVEMENT | US12569209 | 2009-09-29 | US20100170987A1 | 2010-07-08 | Cedric Meyer |
| An aircraft center section includes a center part of an aircraft fuselage, a wing section, a center wing box installed at least partly in the fuselage and providing a junction between the wing section and the fuselage, and a ventral fairing partly enveloping the fuselage and the wing section, with the ventral fairing being attached directly to the wing section and to the fuselage by means of structural elements that can make the ventral fairing a working fairing. | ||||||
| 266 | FAIRING SYSTEM FOR A HORIZONTAL STABILISER OF AN AIRCRAFT AND PROCESS FOR INSTALLING SAID SYSTEM | US12395831 | 2009-03-02 | US20100163672A1 | 2010-07-01 | Gonzalo RAMIREZ BLANCO; Jose Luis Lozano Garcia |
| The invention relates to a fairing system for a horizontal stabiliser of an aircraft and to a process for installing said system, such that the fairing system for the sealing of the horizontal stabiliser (2) and the fuselage (1) of the aircraft comprises a primary fairing (50, 51) arranged on the horizontal stabiliser (2) of the aircraft, the mentioned primary fairing (50, 51) being solidly connected to the mentioned horizontal stabiliser (2) which is in turn trimmable with respect to the fuselage (1), the fairing system in turn comprising a secondary fairing (80, 81) such that the primary fairing (50, 51) is coupled to the horizontal stabiliser (2) through supports (30) arranged in the direction of the chord of the primary fairing (50, 51), said supports (30) being located in the outer part of said primary fairing (50, 51) with respect to the fuselage (1), the secondary fairing (80, 81) being arranged in the outer part of the supports (30), the purpose of said secondary fairing (80, 81) being to cover the mentioned supports (30) and offer a good aerodynamic performance of the assembly. The invention also relates to a process for installing such a fairing system on the horizontal stabiliser (2) of an aircraft. | ||||||
| 267 | Landing gear with noise reduction fairing | US12458407 | 2009-07-10 | US20100155529A1 | 2010-06-24 | Leung Choi Chow; Philip Campbell; Christopher Wood; Andrew John Dyer |
| An aircraft noise reduction apparatus is provided which includes an aircraft landing gear assembly and a noise reduction fairing 12. The landing gear assembly comprises a landing gear 10 arranged to be moveable between a stowed position and a fully deployed position. The noise reduction fairing 12 may comprise a wrap-around fairing which, when the landing gear 10 is in its fully deployed position, wraps around the landing gear 10 and extends along the majority of the length of a landing gear leg 11. A landing gear bay door assembly 16, 17 comprising at least one door may also be provided. The fairing 12 may have a recess 24 for accommodating one of landing gear bay doors when the door 16 is in its fully open position. | ||||||
| 268 | Reinforced cover for gaps in an aerodynamic contour | US11825661 | 2007-07-05 | US07669800B2 | 2010-03-02 | Agustín Mariano Martín Hernández |
| Reinforced cover for gaps in an aerodynamic contour of a vehicle, with a first attachment section 1a attachable to a structural element 2, 5 of the vehicle 11, on a first axial plane I; a second elastic section 1c which covers a gap 3 which is located between a fixed part 5 and a moving part 6, 12 of the vehicle 11, and provided with a low-friction coating 8 on its inner surface 1e, an outer surface 1k with a fiberglass layer 7a; a main internal body 9 of an elastic material, a flexible transition section 1g between the first and the second section, 1a, 1c; the outer surface 1k of the second section 1c flushing with the outer surface 5a and extending towards the free end 1d as a continuation of the outer surface 5a of the fixed part 5. | ||||||
| 269 | METHOD OF REDUCING THE COMPRESSIBILITY DRAG OF A WING, AND CONTAINER INPLEMENTING THE METHOD | US12255296 | 2008-10-21 | US20100044519A1 | 2010-02-25 | Thierry FOL; Cyrll 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). | ||||||
| 270 | ANTENNA FAIRING AND METHOD | US12033356 | 2008-02-19 | US20100038488A1 | 2010-02-18 | Stanley D. Ferguson; William W. Herling; David A. Treiber |
| A fairing suitable for enclosing a component mounted on an exterior surface of a mobile platform, and more particularly on an outer surface of a high speed mobile platform such as a jet aircraft or an aerospace vehicle. The fairing provides aggressive closure angles for optimum RF performance when used to house an antenna that is scanned to varying azimuth and elevation angles. The fairing further provides low aerodynamic drag, is scalable to enclose components having wide ranging dimensions, and provides attached flow with minimum separation of airflow thereover for airflows experienced by high speed jet aircraft, and reduces or eliminates RF reflections within the fairing from the RF beam of the antenna. | ||||||
| 271 | Torque link set | US12458242 | 2009-07-06 | US20100012778A1 | 2010-01-21 | Leung Choi Chow; Philip Campbell; Christopher Neil Wood |
| An aircraft landing gear (10) includes a torque link set (12) comprising a first fairing (12a) rotatably connected at a first end (18) to a first end (19) of a second fairing (12b). The fairings (12a), (12b) may be arranged to act as first and second torque links. The fairings may be in the form of noise reduction fairings. | ||||||
| 272 | FAIRING AND AIRFOIL APPARATUS AND METHOD | US12128123 | 2008-05-28 | US20090321572A1 | 2009-12-31 | Stanley D. Ferguson; William W. Herling; David A. Treiber |
| An airfoil for use on a high speed, jet powered airborne mobile platform and secured to an exterior surface of said mobile platform at a location so as to be disposed within a boundary layer during flight of the mobile platform. The airfoil produces a peak Mach number for airflow over a longitudinal centerline of said airfoil that is no greater than about Mach 1.2 when said mobile platform is moving at a speed of about Mach 0.85 with a relative constant Mach number flow over a region defined as at least an approximate 20% length of maximum thickness of said airfoil. The airfoil also has a pressure distribution (Cp) that is positive at a trailing edge thereof. | ||||||
| 273 | Aircraft noise reduction apparatus | US12153493 | 2008-05-20 | US20090321559A1 | 2009-12-31 | Leung Choi Chow; Christopher Neil Wood; Philip Campbell |
| The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear. | ||||||
| 274 | AERODYNAMIC SHROUD HAVING TEXTURED SURFACE | US12088770 | 2006-09-27 | US20090304511A1 | 2009-12-10 | William W. Brannon, III |
| An aerodynamic shroud positionable surrounding a hub to which blades are attached is disclosed. The shroud has a textured outer surface that is configured so as to create a turbulent boundary layer for fluid flowing over the surface. The turbulent boundary layer delays flow separation from the shroud and reduces drag. The shroud may be formed from a domed shell mounted on the hub and have skirts that surround the hub. The textured surface is provided by dimples in the surface or projections from the surface. The shroud is intended to reduce main and tail rotor hub drag on helicopters but is also useful on marine propellers, aircraft propellers and jet engine fans. | ||||||
| 275 | Seal assemblies for use with drooped spoilers and other control surfaces on aircraft | US11220446 | 2005-09-07 | US07611099B2 | 2009-11-03 | Jan A. Kordel; Seiya Sakurai; Bret A. Bowers; Christopher G. Glassmoyer; Darren B. Williams |
| Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion. | ||||||
| 276 | Flight surface seal | US12382472 | 2009-03-17 | US20090267304A1 | 2009-10-29 | Eric Wildman |
| A seal for sealing a gap between a first (252) and a second (207) component of an aircraft flight surface which has a first seal body (222) having a first sealing portion (246) arranged to seal against the first component, wherein the first seal body is movably mounted to the second component so as to seal at least part of the gap during relative movement of the first and second components. A seal is also provided with components movable relative to each other. | ||||||
| 277 | METHODS AND APPARATUS FOR OPTICAL PROPAGATION IMPROVEMENT SYSTEM | US12359064 | 2009-01-23 | US20090242702A1 | 2009-10-01 | 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. | ||||||
| 278 | ENVIRONMENTAL CONTROL SYSTEM PACK PALLETS | US12047179 | 2008-03-12 | US20090230243A1 | 2009-09-17 | Donald E. Army; Frederick Peacos; John Polifka; Michael Zager |
| An Environmental Control System (ECS) includes a pallet which supports at least one ECS component. The pallet defines a pallet surface that matches an aircraft outer mold line. | ||||||
| 279 | VIBRATION DAMPING FOR WING-TO-BODY AIRCRAFT FAIRING | US12395648 | 2009-02-28 | US20090184200A1 | 2009-07-23 | Juhn-Shyue Lin; Herbert L. Hoffman; Gary R. Chewning; Melvin Kosanchick, III; Hugh Poling |
| A wing-to-body fairing for aircraft is formed from a sandwich structure having integrated vibration damping. | ||||||
| 280 | Elastic pre-deformed fairings for aircrafts | US11435364 | 2006-05-16 | US07510144B2 | 2009-03-31 | Juan Carlos Ambite Iglesias; Fernando Martin Prieto; Miguel Angel Calero Gallardo; Antonio Cala Romero |
| A fairing for streamlining the junction between the horizontal stabilizer and the fuselage or the fin of an aircraft, comprising an upper fairing shell, a lower fairing shell, a leading edge extension, and several fittings to join the upper and lower fairing shells to the horizontal stabilizer. The upper and lower fairing shells are solid laminates of composite material that are designed with a shape, composition, and thickness such that they can be elastically deformed when they are fitted to the horizontal stabilizer, providing a contact force permitting them to lay permanently in contact with the fuselage or fin. A process for manufacturing the fairing shells. | ||||||
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