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公开(公告)号：US20190337606A1
公开(公告)日：2019-11-07
申请号：US15968649
申请日：2018-05-01
摘要： An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.
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公开(公告)号：US10442523B2
公开(公告)日：2019-10-15
申请号：US14835659
申请日：2015-08-25
申请人： The Boeing Company
摘要： Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.
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公开(公告)号：US10260417B2
公开(公告)日：2019-04-16
申请号：US14977854
申请日：2015-12-22
摘要： A turboprop assembly includes a nacelle with a main nacelle body and a nacelle extension coupled to the main nacelle body. The nacelle extension has a wall that defines an air intake port. The air intake port has a non-circular, non-rectangular, and non-oval shaped perimeter extending in two of three dimensions.
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公开(公告)号：US20190061966A1
公开(公告)日：2019-02-28
申请号：US15689304
申请日：2017-08-29
发明人： Randall Ray West
摘要： A nacelle mounted above a wing of an aircraft. A support structure on the nacelle above the pylon resists forces in different directions, and includes door supports allowing the door to be opened upwardly. A retaining structure on the pylon below the nacelle resists forces in different directions, and includes a fixed support track and multiple keepers. Each keeper includes a first end which slides within the channel, and a second end which engages a latch on the closed door. A pylon below the nacelle supports the nacelle and an engine in the nacelle above the wing, increases aerodynamic efficiency, and may include a side spar for supporting the engine from the side. A fire seal assembly includes a depressor surface and a fire seal, and the latter does not contact the former until the door is almost closed, so that compression is substantially direct and scrubbing is reduced.
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公开(公告)号：US10093436B2
公开(公告)日：2018-10-09
申请号：US15191143
申请日：2016-06-23
摘要： An engine communication system for aircraft engines having a nacelle with two cowlings extending annularly about the aircraft engine and defining a radially outward surface thereof, and at least one sensor positioned radially inward from the nacelle. The system includes a cowling gap positioned between the two cowlings when coupled together, and an engine control device communicatively coupled to the sensor and configured to at least one of receive engine data from the sensor and receive instruction data from a transmitter device positioned radially outward from the cowling gap. The system also includes a linearly polarized antenna communicatively coupled to the engine control device and positioned radially inward from the cowling gap and extending radially outward toward the cowling gap. The antenna is configured to at least one of receive and transmit the engine data and the instruction data through the cowling gap.
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公开(公告)号：US10086936B2
公开(公告)日：2018-10-02
申请号：US15269853
申请日：2016-09-19
摘要： A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.
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公开(公告)号：US20180057159A1
公开(公告)日：2018-03-01
申请号：US15252545
申请日：2016-08-31
摘要： A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.
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公开(公告)号：US09873504B2
公开(公告)日：2018-01-23
申请号：US14057828
申请日：2013-10-18
申请人： Rohr, Inc.
发明人： Michael Aten
摘要： A cowl for use in a nacelle is provided. The nacelle at least partially surrounds an engine that extends circumferentially about an axially-extending engine centerline. The cowl includes a first side portion and a second side portion. The first and second side portions each are pivotably connected to the nacelle proximate a top of the nacelle. The first and second side portions are configured so that they abut one another to form an external split line proximate the top of the nacelle.
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公开(公告)号：US20170292882A1
公开(公告)日：2017-10-12
申请号：US15095199
申请日：2016-04-11
发明人： Joshua V. Wood , Michael Joseph Murphy , Justin R. Urban , Robert E. Malecki , William W. Rice , David W. Lamarre
CPC分类号： G01L5/133 , B64C7/02 , B64D27/10 , F01D21/003 , F02K1/15 , F05D2260/50 , F05D2270/80 , F05D2270/821 , G01M15/14
摘要： A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.
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公开(公告)号：US09611807B2
公开(公告)日：2017-04-04
申请号：US14484684
申请日：2014-09-12
申请人： AIRCELLE
摘要： A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.
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