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 |
|---|---|---|---|---|---|---|
| 161 | LOAD-BEARING FAIRING ELEMENT FOR A FLAP ADJUSTMENT MECHANISM AND AIRCRAFT HAVING SUCH A FAIRING ELEMENT | US14713089 | 2015-05-15 | US20170247104A2 | 2017-08-31 | TAMAS HAVAR; Mirko MISSBACH; Wolfgang MACHUNZE |
| A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in. Consequently there is no need to provide complex stiffening structures within the fairing element. | ||||||
| 162 | Seal assembly | US14969422 | 2015-12-15 | US09745049B2 | 2017-08-29 | James Wilson; Alan Quayle; Paul Hadley |
| A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position. | ||||||
| 163 | INDEPENDENT CONTROL FOR UPPER AND LOWER ROTOR OF A ROTARY WING AIRCRAFT | US15504525 | 2015-09-30 | US20170233067A1 | 2017-08-17 | Ezra Eller; Matthew A. White; David H. Hunter |
| An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer. | ||||||
| 164 | ACTIVE AIRFLOW SYSTEM AND METHOD OF REDUCING DRAG FOR AIRCRAFT | US15262671 | 2016-09-12 | US20170225772A1 | 2017-08-10 | ByungYoung Min; Barbara Brenda Botros; Razvan Virgil Florea; Patrick Bowles; Claude G. Matalanis; Brian E. Wake |
| A rotary wing aircraft includes a fuselage having a plurality of surfaces. At least one engine is mounted in the fuselage. A rotor assembly includes a rotor shaft a plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. An active air discharge opening extends through one of the plurality of surfaces of the fuselage and one of the plurality of surface portions of the rotor assembly, and an active air generation system is mounted in the fuselage. The active air generation system is configured and disposed to generate and direct a flow of air through the active air discharge opening to disrupt an airstream flowing over the one of the plurality of surfaces of the fuselage and the one of the plurality of surface portions of the rotor assembly. | ||||||
| 165 | VORTEX GENERATORS AND METHOD OF CREATING VORTICES ON AN AIRCRAFT | US15265502 | 2016-09-14 | US20170174326A1 | 2017-06-22 | Patrick Bowles; Barbara Brenda Botros; ByungYoung Min; Claude G. Matalanis; Brian E. Wake |
| A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft, and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A plurality of vortex generators is mounted relative to at least one of the plurality of surfaces of the fuselage and the plurality of surface portions of the rotor assembly. The plurality of vortex generators operate to disrupt a boundary layer of air flowing over the one of the plurality of surfaces and the plurality of surface portions to reduce drag on the one of the fuselage and the rotor assembly. | ||||||
| 166 | ROTARY WING VEHICLE | US15175161 | 2016-06-07 | US20170166305A1 | 2017-06-15 | Paul E. Arlton; David J. Arlton |
| A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight. | ||||||
| 167 | Stiffened panel and method of manufacturing same | US14426955 | 2013-09-09 | US09643713B2 | 2017-05-09 | Michel Bermudez; Didier Mesnage; Hichem Smaoui; Benoit Fleury |
| A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method. | ||||||
| 168 | Fairing transition and vehicle with a movable body and a fixed body comprising a fairing transition | US13420047 | 2012-03-14 | US09637219B2 | 2017-05-02 | Sascha Timm; Gerd Stahl; Uwe Henning |
| A fairing transition is provided for covering a gap between a movable body and a fixed body on a vehicle that includes, but is not limited to a base plate that is attachable to a vehicle, a cover plate that is attachable to the base plate. The base plate and the cover plate include, but are not limited to a correspondingly formed connecting profile having positive fit on surfaces that face each other, with the connecting profile configured to slide the cover plate onto the base plate. Furthermore, the cover plate is lockable to the base plate in an end position. | ||||||
| 169 | Air seal assembly for aircraft flap seal | US14284356 | 2014-05-21 | US09618118B2 | 2017-04-11 | Scott Robert Foster; Eiji Sugi; Harold Demarest, Jr. |
| An air seal assembly for an aircraft control surface comprises a bulb-type air seal, a mounting bracket and a fastener. The bulb-type air seal has a hollow bulb portion, a T-shaped mounting extension, and a first through hole extending through the T-shaped mounting extension. The mounting bracket has a T-shaped channel configured to slidingly receive the T-shaped mounting extension of the air seal and a second through hole. The fastener has a head at one end and an opposite exposed end sized for extending through the first through hole in the T-shaped mounting extension and through the second through hole in the mounting bracket. The exposed end is accessible to tighten the fastener against the bracket to keep the air seal in place within the T-shaped channel. | ||||||
| 170 | Internal locking mechanism for a hold open rod | US13345239 | 2012-01-06 | US09599137B2 | 2017-03-21 | Ryan A. Wheeler; Julio Palma |
| A hold open rod may include: an inner member; an outer member configured to have the inner member slide in and out of the outer member; a locking mechanism including a portion attached to the outer member and a portion attached to the inner member; a locking plug configured to move axially along an axis of the inner, outer members; a locking dog configured to move radially between a locking position and an unlocking position and a release cable operatively connected to the locking plug and configured to move the locking plug to the unlocking position. A method of actuating a lock mechanism on a hold open rod may also be provided. | ||||||
| 171 | Self-tuning tunable mass dampers | US14840024 | 2015-08-30 | US09587699B1 | 2017-03-07 | Steven F. Griffin; Daniel Niedermaier |
| A tunable mass damper incorporates a frame and a voice coil supported in the frame. A magnet concentric with the voice coil is movable relative to the housing via the voice coil. A plurality of flexures having a first end extending from the magnet and an arm releasably coupled to the frame are adjustable to an effective length for a desired frequency of reciprocation of the magnet. | ||||||
| 172 | DEFLECTOR ASSEMBLY FOR AN AIRCRAFT | US15236565 | 2016-08-15 | US20170057617A1 | 2017-03-02 | Kaspar VON-WILMOWSKY; Gerald ERNST |
| A deflector assembly for the rope/cable hanging from a hoist mounted on an aircraft (A). The deflector assembly has an adjoined anchorage that includes a socket face that internally has a sliding bearing in which is housed an innermost end, so that the innermost end is slidably guided relative to the adjoined anchorage to have one degree of freedom along a linear translation axis (LT). A remote anchorage has a support bracket for demountably mounting the remote anchorage to the fuselage. The rotorcraft can be chosen among: helicopters, hybrid rotary aircrafts, UAV rotorcrafts and inhabitable rotorcrafts including remote piloting functions. | ||||||
| 173 | VEHICLE FAIRING INCLUDING AN ELECTRICAL ROUTING | US15222703 | 2016-07-28 | US20170028947A1 | 2017-02-02 | Jack BLANCHARD; Anthony BRYANT |
| A vehicle fairing including an electrical routing for conducting power and/or control signals between spaced-apart components of a vehicle structure. The vehicle fairing includes an outer surface configured to form part of an outer surface of a vehicle body. The electrical routing includes a printed circuit board having a substrate and a first conductive path for conduction of electrical current or signals provided on the substrate. The substrate is substantially rigid and forms at least a portion of the outer surface of the vehicle fairing. | ||||||
| 174 | AIRCRAFT EXTERNAL PART WITH INFLATABLE PANELS | US15201762 | 2016-07-05 | US20170001703A1 | 2017-01-05 | Jesús Javier VAZQUEZ CASTRO; Fernando PEREIRA MOSQUEIRA; Juan José GUTIERREZ SANTIAGO; Anthony LANGLEY; Guy TOTHILL; Davood SARCHAMY; Miguel MARÍN MUÑOS |
| An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements. | ||||||
| 175 | Landing Gear Noise Abatement Devices | US14048914 | 2013-10-08 | US20160375990A1 | 2016-12-29 | Rony Giovanni Ganis |
| A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag. | ||||||
| 176 | COMPOSITE SLAT CAN ASSEMBLY AND METHODS OF MAKING SAME | US15172964 | 2016-06-03 | US20160362174A1 | 2016-12-15 | William L. Rodman; Wouter T. Gerber; Jacobus Frederik Swart |
| A slat can assembly with a slat can body includes at least one full ply of a composite fiber sheet material and a plurality of elongated, unidirectional fiber ply strips that are arranged into the shape of the slat can body. At least some of the unidirectional fiber ply strips are laid over the full ply. And, the full ply and the elongated, unidirectional fiber ply strips cooperate to provide a contoured shape defined by a cellular core member. | ||||||
| 177 | FASTENING DEVICE | US15166464 | 2016-05-27 | US20160347439A1 | 2016-12-01 | Richard CHRISTENSEN; Harish AGADI; Lee RANDLE |
| The invention relates to an aircraft structure, the aircraft structure comprising a first component and a second component. A fastening device fastens the first component to the second component, wherein the fastening device comprises a clamping member, and a fastening member. The fastening member has a longitudinal axis, and the clamping member is associated with the first component such that the clamping member is movable in a first direction and is fixed in position in a second direction, the first direction being parallel to the longitudinal axis of the fastener, wherein the fastener extends through the second component into engagement with the clamping member and holds the clamping member against the second component. The fastening device may hold the first component and second component in a fixed position relative to one another, in at least one direction, without applying a clamping force between the first component and second component. | ||||||
| 178 | Motion-damping systems between base structure and an attached component and methods including the same | US14104992 | 2013-12-12 | US09509204B2 | 2016-11-29 | John Ralph Hull; Michael Strasik; Thomas H. Martig |
| Motion-damping systems and methods that include motion-damping systems are disclosed herein. The motion-damping systems include a flexible body that is configured to extend within a gap that is defined between a base structure and an attached component. The motion-damping systems further include a magnetic assembly and a ferromagnetic body. One of the magnetic assembly and the ferromagnetic body is located within the flexible body and the other of the magnetic assembly and the ferromagnetic body is operatively affixed to a selected one of the base structure and the attached component. The magnetic assembly and the ferromagnetic body are oriented such that a magnetic force therebetween retains the flexible body in physical contact with the selected one of the base structure and the attached component. The methods include methods of installing and/or operating the motion-dampening systems. | ||||||
| 179 | Retractable equipment system including a device optimized for driving protection flaps | US14092194 | 2013-11-27 | US09493229B2 | 2016-11-15 | Michel L'Heritier; Eric Doustens; Philippe Bosc; Philippe Castagne |
| A system for retractable equipment including movable protection flaps in which a flap drive device serves to drive the flaps in optimized movement, providing a mechanical coupling between the flaps and the retractable equipment such that a common motor member can be used for driving both the equipment and the flaps between respective retracted and deployed positions. The flap drive device includes a cam in the form of a sliding channel secured to a frame of the system and a cam follower in the form of a translating pivot mechanically coupled to both the retractable equipment and a flap drive member. The path followed by the retractable equipment is accordingly optimized. | ||||||
| 180 | Variable-width aerodynamic device | US14136350 | 2013-12-20 | US09457894B2 | 2016-10-04 | André dos Santos Bonatto; Francisco Keller Klug; Julio Romano Meneghini; Leandro Guilherme Crenite Simões; Miacel Gianini Valle Do Carmo; Rafael dos Santos 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. | ||||||
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