| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Break-away suppression device | JP11459596 | 1996-05-09 | JPH09303331A | 1997-11-25 | FUJINO MICHINORI; KAWAMURA YUICHI |
| PROBLEM TO BE SOLVED: To provide a break-away suppressing means which does not require a large-scale improvement of an air frame structure, the means preventing a break away of a stream at a place where a disorder of air stream is drastic. SOLUTION: A small piece 5 is attached at a suppression angle αwhich reduces a speed of a flow of a part A where the flow rate is rapid on an upper surface of a main wing in the vicinity of a part (maximum load point) A where the flow rate which flows along the surface of a pylon 2 is the most rapid in order to prevent the break away of the flow at an interference part 4 of an aircraft where an engine nacell 3 is connected to the upper surface of the main wing via the pylon 2. Consequently, a speed difference of a flowing body which flows on the surface of the pylon 2 is eliminated (alleviating a pressure inclination) thereby suppressing the break-away. | ||||||
| 102 | Combination of aircraft and power plant | JP1055188 | 1988-01-20 | JPS63195099A | 1988-08-12 | JIYON ARUBAATO MARINZU |
| 103 | Lift keeping mechanism in aircraft | JP25838884 | 1984-12-05 | JPS60139597A | 1985-07-24 | ROBAATO PERAN; PIEERU JIYUURUDAN; BERUNAADO POORII |
| 104 | Nacelle device | JP21852582 | 1982-12-15 | JPS58122294A | 1983-07-20 | DONARUDO JIYON DOUUSA; KONRADO DADORII WAAGENKUNEHITO |
| 105 | Reducing member for drag | JP11856280 | 1980-08-29 | JPS5650898A | 1981-05-08 | JIYON TOOMASU KUTONEI |
| 106 | EJECTOR AND AIRFOIL CONFIGURATIONS | PCT/US2016044326 | 2016-07-27 | WO2017065858A3 | 2017-07-13 | EVULET ANDREI |
| A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface. | ||||||
| 107 | EXTREMELY QUIET SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT | PCT/US2016026680 | 2016-04-08 | WO2016209331A2 | 2016-12-29 | RAHRIG KYLE; SOMMER GEOFFREY; WAINFAN BARNABY S |
| An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage. | ||||||
| 108 | NACELLE WITH SIMPLIFIED COWLING ARRANGEMENT | PCT/FR2008001390 | 2008-10-03 | WO2009090327A2 | 2009-07-23 | JORET JEAN-PHILLIPPE; BAILLARD ANDRE; CLERE GERARD |
| The invention relates to a nacelle (1) that comprises a first cowling (7) and a second cowling (9) capable of covering in particular the area (15) located around the casing of the fan (19) of a turbojet engine (3). The nacelle further includes an intermediate cowling (23) attached to said first cowling (7) so as to sandwich a mast (5) holding said turbojet engine (3). The second cowling (9) is mounted onto the intermediate cowling (23) via removable fastening means. | ||||||
| 109 | NACELLE | PCT/US2013044851 | 2013-06-07 | WO2013185118A4 | 2014-02-20 | JAMES NORMAN JOHN |
| A nacelle configured to be coupled to an underside of a wing so as to form a clearance space therebetween includes at least a lip defining an inlet and a first cowling disposed aft of the lip. The first cowling has an outer surface with at least one concave region that is depressed relative to another region of the outer surface. In some aspects, the depressed region can be disposed on an inboard side of the wing, for example, on an upper surface of the first cowling facing a wing. The nacelle can include a second cowling disposed between the lip and the first cowling and the first cowling can translate in a longitudinal direction relative to the second cowling. | ||||||
| 110 | ENGINE NACELLE OF AN AIRCRAFT COMPRISING A VORTEX GENERATOR ARRANGEMENT | PCT/EP2008004841 | 2008-06-16 | WO2008151843A4 | 2009-02-26 | SCHWETZLER DETLEV |
| An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators (3, 4, 5) so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators (3, 4, 5) overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor (K31) situated between two boundary lines (51, 52), wherein: the starting point (51 a) of the first boundary line (51) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (51 b) of the first boundary line (51 ) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L·2/3; the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L·2/3. | ||||||
| 111 | SYSTEMS AND METHODS FOR REDUCING NOISE FROM JET ENGINE EXHAUST | PCT/US2008052527 | 2008-01-30 | WO2008100712A2 | 2008-08-21 | ALKISLAR MEHMET B; BUTLER GEORGE W; REED DAVID H |
| Jet engine nozzles with projections (e.g., chevrons) and injected flow, and associated systems and methods are disclosed. A method in accordance with one embodiment includes generating a first flow of gas with a jet engine, delivering the first flow through a nozzle having a trailing edge perimeter that includes multiple projections extending in an aft direction, and injecting a pressurized second flow of fluid into the first flow proximate to the projections. In other embodiments, other mixing enhancement devices (e.g., vortex generators) are carried by the projections. It is expected that the combination of the projections and the mixing enhancement devices will reduce engine exhaust noise levels below the levels achievable with either projections or injected flow individually. | ||||||
| 112 | INTEGRATED AND/OR MODULAR HIGH-SPEED AIRCRAFT | PCT/US0201567 | 2002-01-17 | WO02079031A3 | 2003-03-27 | NELSON CHESTER P |
| An integrated and modular high-speed aircraft (200) and method of design and manufacture. The aircraft (200) can have a supersonic or near-sonic cruise Mach number. In one embodiment, the aircraft (200) can include an aft body integrated with a delta wing (204) and a rearwardly-tapering fuselage (202) to define a smooth forward-to-rear area distribution. A propulsion system (206), including an engine (216), inlet (220), and exhaust nozzle (222) can be integrated into the aft body to be at least partially hidden behind the wing (204). In one embodiment, the entrance of the inlet can be positioned beneath the wing (204), and the exit of the nozzle (222) can be positioned at or above the wing (204). An S-shaped inlet duct (221) can deliver air to the aft-mounted integrated engine. | ||||||
| 113 | AFT PYLON FAIRING FOR AIRCRAFT | PCT/IB2014000223 | 2014-02-28 | WO2014135948A3 | 2014-11-27 | SHEPHARD KEVIN; YOUNG JEFFREY E; BEEDY LYLE |
| Aft fairings (22) for aircraft pylons (14) are disclosed. In one example, a fairing (22) comprises: two opposite side panels (24) extending generally along a longitudinal direction of the fairing (22); a plurality of transverse ribs (28) interconnecting the two opposite side panels (24); and a heat shield (30) for exposure to a primary flow (16) of an aircraft engine (10). The heat shield (30) comprises transversely opposed side end portions (30A, 30C) and a mid portion (30B) disposed between the transversely opposed side end portions (30A, 30C). The heat shield (30) is secured to the ribs (28) via the mid portion (30B) of the heat shield (30). The transversely opposed side end portions (30A, 30C) are permitted to move outwardly from the mid portion (30B) due to thermal expansion of the heat shield (30). | ||||||
| 114 | TURBO ENGINE ATTACHMENT PYLON | PCT/FR2012052439 | 2012-10-24 | WO2013064768A3 | 2013-12-27 | BODARD GUILLAUME; HENRY CYPRIEN; JODET NORMAN; VUILLEMIN ALEXANDRE ALFRED GASTON |
| A turbo engine attachment pylon configured to connect a turbo engine to a structural element of an aircraft, said pylon (30) having an aerodynamic profile defined by two opposite lateral faces and delimited longitudinally between a leading edge (31) and a trailing edge (33). The pylon (30) comprises, on each of the lateral faces (36) thereof, a series of deflectors (40) spaced transversely apart from one another and between them defining two converging curved channels (60) configured to accelerate the air flow circulating inside the channels (60) when the aircraft is taking off or during flight, and to divert said air flow towards the jet of the turbo engine. | ||||||
| 115 | AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE | PCT/FR2008052165 | 2008-12-01 | WO2009077689A3 | 2009-08-20 | CHELIN FREDERIC; SURPLY THIERRY; BOURDEAU CHRISTOPHE |
| The invention relates to an aircraft leading edge including, as an extension, an aerodynamic surface at which flows an aerodynamic flow and where are provided air outlets (30) for preventing the separation of said aerodynamic flow, the air outlets (30) being arranged into at least two rows substantially parallel to the leading edge and in an offset manner for at least two successive layers, characterised in that it comprises at least one shim (36) provided between two walls defining the aerodynamic surface, said shim having, on the one hand, an outer surface (38) arranged as an extension of the aerodynamic surface (26), a first inclined surface (40) in contact with the first wall defining the aerodynamic surface, and a second inclined surface (42) in contact with the second wall defining the aerodynamic surface and, on the other hand, protruding and/or recessed patterns formed at the inclined surfaces (40, 42) and alternating from one face to the other, that allow the passage of air on either side of the aerodynamic surface. | ||||||
| 116 | AIRCRAFT ENGINE INLET HAVING ZONE OF DEFORMATION | PCT/US2007072710 | 2007-07-03 | WO2008085542A3 | 2008-10-02 | SHUTRUMP JEFFREY D |
| The present invention relates to an inlet assembly for a turbofan engine nacelle and to a method of manufacturing an inlet assembly for an aircraft engine nacelle. An inlet assembly (17) for an aircraft engine nacelle (1) includes an inner barrel (39), an outer barrel (41) radially spaced from the inner barrel, and a rear support (35) for supporting the outer barrel relative to the inner barrel. The rear support (35) includes at least one radially extending stiff ener (63) and at least one energy absorber (67) defining a zone of deformation (71) adjacent the inner barrel (39). The rear support (35) is deformable in the zone of deformation (71) in response to forces applied during a fan blade-out event to prevent fracture of the rear support. | ||||||
| 117 | TILTROTOR AIRCRAFT WITH OUTBOARD FIXED ENGINES | US15621686 | 2017-06-13 | US20180354616A1 | 2018-12-13 | Kirk L. Groninga; Daniel B. Robertson |
| In a first aspect, there is a rotor system for a tiltrotor aircraft, the rotor system including an upper outboard engine in a fixed location on a wing member of the tiltrotor aircraft; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. In another aspect, there is provided a tiltrotor aircraft including a fuselage; a wing member; an upper outboard engine in a fixed location on the wing member; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. | ||||||
| 118 | Electric propulsion assembly for an aircraft | US14898127 | 2014-06-13 | US10138899B2 | 2018-11-27 | Emmanuel Joubert; Hichem Smaoui; Charles Nespoulous; Bruno Rechain |
| An electric propulsion assembly for an aircraft includes a nacelle having a nacelle cowl which defines an inner space for arranging an electric propulsion unit, which includes a blower, of the aircraft. An electric motor assembly is placed in the inner space and connected to the propulsion unit to supply power to the propulsion unit. An airflow generated by the blower flows in a space between the motor assembly and the nacelle cowl defining a duct to supply thrust to the aircraft. A power electronics system has at least one heat exchanger to transfer thermal energy from the system to a work fluid to cool the system. The heat exchanger is placed to project at least partially into the duct, so that the work fluid consists of the air flow generated by the blower. | ||||||
| 119 | Distributed electric ducted fan wing | US15374771 | 2016-12-09 | US10099793B2 | 2018-10-16 | David G. Ullman; Vincent Homer |
| The Distributed Electric Ducted Fan Wing concept incorporates multiple electric ducted fans on lifting surfaces configured to provide integrated aerodynamics and propulsion resulting in enhanced aerodynamic characteristics and thus aircraft performance. The concept uses a plurality of electric ducted fans (EDFs) to not only provide thrust, but to also blow air across the upper surface of a substantial portion of the lifting surface area increasing lift at little loss in efficiency. Not only can the total lift on the surfaces be enhanced, but the lift distribution managed: to aid in aircraft control; ameliorate the effects of turbulence: reduce shed vortices; mitigate the effects of system failures; eliminate stalls; and compensate for crosswinds. This concept offers the potential for increasing electric airplane efficiency and performance, enhancing Short Takeoff and Landing (STOL) capabilities, improving passenger comfort, and reducing the structural stress and cost of aircraft. | ||||||
| 120 | Latch beam deflection support | US14793024 | 2015-07-07 | US10093429B2 | 2018-10-09 | 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. | ||||||
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