| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Aircraft Hydraulic Systems Having Shared Components | US15466655 | 2017-03-22 | US20180274563A1 | 2018-09-27 | Carl Theodore Elving; Robert Paul Reynolds; David Alan Hawthorne; Carlos Alexander Fenny |
| A hydraulic system for an aircraft having an engine and an auxiliary power unit includes a first hydraulic subsystem including a first hydraulic pump and a first set of hydraulic-powered components in fluid communication with the first hydraulic pump. The first hydraulic pump is powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components. The hydraulic system includes a second hydraulic subsystem including a second hydraulic pump and a second set of hydraulic-powered components in fluid communication with the second hydraulic pump. The second hydraulic pump is powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components. A shared return line subsystem and reservoir is in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid to the first and second hydraulic pumps. | ||||||
| 122 | Vertical take-off and landing (VTOL) aircraft with exhaust deflector | US14987295 | 2016-01-04 | US10077108B2 | 2018-09-18 | Timothy Fred Lauder |
| A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions. | ||||||
| 123 | BOGIE MECHANISM FOR A TILTROTOR PROPROTOR DOOR | US15448136 | 2017-03-02 | US20180252264A1 | 2018-09-06 | Nick Pravanh; Michael E. Rinehart; Bart Shafer; Clegg Smith; Jeffrey M. Williams |
| A door roller mechanism for cooperation with a roller track including a carriage member having a door attachment feature; at least one roller disposed for rotation on a first side of the carriage member when the carriage member moves in the rolling direction; at least one roller disposed for rotation on an opposite second side of the carriage member when the carriage member moves in the rolling direction; a first rub member disposed on the first side of the carriage; a second rub member disposed on the second side of the carriage; and at least one biasing element disposed on the carriage member for resiliently biasing the first rub member and the second rub member in opposite lateral directions so as to contact a respective first track surface and a second track surface in a manner to dampen lateral vibration of a door connected to the roller mechanism. | ||||||
| 124 | ROLLER TRACK ASSEMBLY FOR A TILTROTOR PROPROTOR DOOR | US15448415 | 2017-03-02 | US20180252263A1 | 2018-09-06 | Nick Pravanh; Michael E. Rinehart; Bart Shafer; Clegg Smith; Bruce B. Bacon |
| A door track assembly for cooperation with a door roller mechanism, including a housing having a longitudinal channel along a length of the housing, wherein the channel descends at an end of the housing to form a stowage recess for the door roller mechanism, and a first track and a second track that are disposed on the housing along a length of the channel and that descend into the stowage recess and along which the door roller mechanism traverses. | ||||||
| 125 | VARIABLE INCIDENT NACELLE APPARATUS AND METHODS | US15379101 | 2016-12-14 | US20180162541A1 | 2018-06-14 | Christopher T. Jasklowski; Omid B. Nakhjavani |
| Variable incident nacelle apparatus and methods are disclosed herein. An apparatus for varying an incident angle of a nacelle of an aircraft engine relative to an aircraft wing comprises a pylon frame member to be rigidly coupled to the aircraft engine. The pylon frame member is to be pivotable about a first axis of rotation. The apparatus further comprises a diagonal brace including a first end defining an aperture to receive a portion of a drive member. The portion of the drive member is to be rotatable relative to the aperture about a second axis of rotation. The drive member includes a pin positioned eccentrically relative to the second axis of rotation. The pin is to be coupled to the pylon frame member to pivot the pylon frame member in response to rotation of the portion of the drive member. | ||||||
| 126 | Aircraft propulsion assembly | US15386954 | 2016-12-21 | US09963999B2 | 2018-05-08 | François Bellet; Cédric Renault; Jérémie Rabineau |
| The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channeling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped. | ||||||
| 127 | Assembly for an aircraft comprising an attachment pylon primary structure formed with three independent elements | US14693545 | 2015-04-22 | US09868543B2 | 2018-01-16 | Olivier Pautis; Jonathan Blanc |
| In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams. | ||||||
| 128 | Aircraft engine mounting system | US15359965 | 2016-11-23 | US09868540B2 | 2018-01-16 | Sergey D. Barmichev; David W. Kirkbride; Mithra M. K. V. Sankrithi |
| An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves. | ||||||
| 129 | SYSTEM FOR INSTALLING AND REMOVING A PROPULSION UNIT ON A PYLON OF AN AIRCRAFT | US15653971 | 2017-07-19 | US20170313432A1 | 2017-11-02 | Patrick BOILEAU; Olivier KERBLER; Julien LEZERAC; Aurélien GONZALEZ; Loïc GRALL; Ludovic TOUPET |
| The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon. | ||||||
| 130 | AIRCRAFT INCLUDING A WING WITH IMPROVED ACOUSTIC TREATMENT | US15471136 | 2017-03-28 | US20170283032A1 | 2017-10-05 | Norman Bruno Andre JODET; Jean-Michel BOITEUX; Jacky Novi MARDJONO |
| An aircraft having a wing and an aeroengine having a longitudinal main axis M and including a ducted nacelle with at least one fan, the wing including an acoustic treatment surface on a bottom portion of its outer shell on either side of the main longitudinal axis M and over a width L perpendicular to the longitudinal axis M that is not greater than three times the diameter D of the fan, the acoustic treatment surface comprising a layer of porous material for attenuating acoustic waves coming from the fan. | ||||||
| 131 | Sound attenuation apparatus and method | US14804577 | 2015-07-21 | US09771868B2 | 2017-09-26 | Eric H. Nesbitt; Justin H. Lan; Thonse R. S. Bhat; Charles W. Rust |
| An aircraft engine sound attenuation apparatus includes a perforated face member, a backing member, a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member, and a bulk absorber disposed in each of the plurality of channels, wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine. | ||||||
| 132 | Sleeved Bolt Assemblies for Aircraft Engine Mount Assemblies | US15410706 | 2017-01-19 | US20170217594A1 | 2017-08-03 | Bruce Bennett Bacon; Michael Edwin Rinehart; Thomas Boudreau |
| A rotorcraft, such as a tiltrotor aircraft having helicopter and airplane modes, includes an airframe, an engine and an engine mount assembly for coupling the engine to the airframe. The engine includes an engine lug forming an aperture. The engine mount assembly includes a mount having an aperture substantially aligned with the engine lug aperture. A sleeved bolt assembly extends through the apertures to secure the engine lug to the mount. The sleeved bolt assembly includes a bolt undersized relative to the apertures forming a circumferential gap within the apertures, a sleeve disposed around at least a portion of the bolt substantially filling the circumferential gap and a nut adapted to thread onto a threaded portion of the bolt. The use of the undersized bolt within the sleeve permits increased clearance between the sleeved bolt assembly and the engine while maintaining strength requirements in high load environments. | ||||||
| 133 | THRUST REVERSER CASCADE SYSTEMS AND METHODS | US14997295 | 2016-01-15 | US20170204810A1 | 2017-07-20 | Naimishkumar B. Harpal; Chen Chuck |
| Systems and methods are provided for a formed thrust reverser cascade. The formed thrust reverser cascade may be coupled to an aircraft propulsor and may include a first portion disposed at a first angle to a portion of the aircraft propulsor and a second portion disposed at a second angle to the first portion. The formed thrust reverser cascade may be circumferentially disposed around a core engine of the aircraft propulsor. The formed thrust reverser cascades may be retrofitted to aircraft propulsors using linear thrust reverser cascade and may increase airflow through the formed thrust reverser cascade due to a greater throat area as compared to the linear thrust reverser cascade. Alternatively, the formed thrust reverser cascades may allow for shorter cascades while retaining the same performance, thus resulting in shorter nacelles. | ||||||
| 134 | COMPLIANT ENGINE NACELLE FOR AIRCRAFT | US15313504 | 2015-05-19 | US20170197712A1 | 2017-07-13 | Mark R. Alber |
| An aircraft includes a fuselage and a wing extending from each lateral side of the fuselage. A nacelle is pivotably se cured to each wing. The nacelle has a rotor located thereat, with the rotor having a rotor tip path plane defined by rotation of the rotor about a rotor axis of rotation. When the rotor tip path plane is changed relative to the wing, the nacelle pivots relative to the wing about a nacelle hinge axis to reduce flapping required by the rotor. A method of operating an aircraft includes changing a rotor tip path plane orientation relative to a wing of the aircraft. The rotor disposed at a nacelle, with the nacelle pivotably secured to the wing. The nacelle is pivoted relative to the wing to reduce an overall tip path plane change requirement of the rotor. | ||||||
| 135 | AIRCRAFT BRACE HOUSING A FLUID TRANSFER LINE | US15387942 | 2016-12-22 | US20170183080A1 | 2017-06-29 | Jaime Genty De La Sagne |
| An aircraft including a wing, a fuselage and at least one brace extending between the wing and the fuselage. The brace houses at least one fluid transfer line between the wing and the fuselage, such as an engine air bleed line, a hydraulic line or a fuel pipe. Use in particular to equip high-winged aircraft. | ||||||
| 136 | AIRCRAFT WITH A STRUT-BRACED FOLDABLE WING | US15301778 | 2015-04-02 | US20170113779A1 | 2017-04-27 | Philip WRIGHT |
| An aircraft (1) including a wing (5), the wing having an inner region (5a) and an outer region (5b), the inner and outer regions (5a, 5b) being connected by a hinge (11) defining a hinge line about which the outer region (5b) is foldable to reduce the span of the wing. The aircraft (1) includes an actuator (13) arranged to actuate the folding of the outer region (5b) of the wing with an actuation force. The wing (5) is braced by an external strut structure (9) for transferring some of the wing loadings in the outer region (5b) of the wing away from the inner region of the wing (5a). The actuator (13) is arranged to exert the actuation force via the strut structure (9). | ||||||
| 137 | AIRCRAFT ENGINE MOUNTING SYSTEM | US15359965 | 2016-11-23 | US20170073078A1 | 2017-03-16 | Sergey D. Barmichev; David W. Kirkbride; Mithra M.K.V. Sankrithi |
| An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves. | ||||||
| 138 | CONTROL SYSTEM AND STRATEGY FOR TAIL SITTER | US15158152 | 2016-05-18 | US20170021924A1 | 2017-01-26 | Stephen Kubik; Joseph T. Driscoll; Frank P. D'Anna; Mark R. Alber; Timothy Fred Lauder; Cody Fegely |
| A tail sitter aircraft is capable of forward flight and hover operations. The tail sitter aircraft includes a wing and first and second prop-nacelles supportively disposed on the wing. Each of the first and second prop-nacelles includes an articulable rotor, which is rotatable about variable rotational axes and which includes blades that are collectively and cyclically controllable in both forward flight and hover regimes. | ||||||
| 139 | LATCH BEAM DEFLECTION SUPPORT | US14793024 | 2015-07-07 | US20170008634A1 | 2017-01-12 | Anthony Lacko |
| An engine nacelle is provided and includes an outer fixed structure (OFS) assembly disposed about an inner fixed structure (IFS) barrel and a latch beam, which is separate from the IFS barrel along an entire length thereof. The latch beam includes forward and trailing ends directly and indirectly supportively coupled to the OFS assembly, respectively. | ||||||
| 140 | Aircraft engine mounting system | US14457287 | 2014-08-12 | US09533768B2 | 2017-01-03 | Sergey D. Barmichev; David W. Kirkbride; Mithra M. K. V. Sankrithi |
| An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves. | ||||||
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