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JP6188836B2 |
The invention is related to an aircraft (1) with a fuselage (2) that defines at least an interior region (2a) and a drive system accommodating region (1f), said drive system accommodating region being arranged inside said fuselage (2) an...
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JP2017137047A |
To provide an aircraft thermal management system that can meet increasingly high cooling demands of future aircraft.A thermal management system 20 for an aircraft is provided. The thermal management system may comprise a first vapor comp...
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JP6176766B2 |
An aircraft with aturbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defimng an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one move...
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JP2017119507A |
To provide a system for sound insulation and impact protection from an open rotor engine.An aircraft (100) includes: a fuselage (102) including a nose (104), a tail (106), a hollow, and an elongate body (108) extending therebetween; a wi...
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JP6128568B2 |
In an intake structure of an aircraft that takes in air from a front side of an airframe, a bump is provided on a surface of the airframe of the aircraft at a portion immediately before an intake. The bump is formed so as to smoothly pro...
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JP2017503951A |
A liquid drain device (10) for an aircraft engine (1), comprising a collector (11) designed to collect the drain liquid from the engine, wherein the device collects the liquid held in the collector. The monitoring means includes pumping ...
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JP6060309B2 |
In some aspects, an aircraft engine thrust reverser lock system includes a pin-capturing member. The pin-capturing member includes a body that is rotatable about an axis defined by a pivot extending through the body. The body includes an...
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JP6043314B2 |
A method of diagnosing a bleed air system fault, where the method includes receiving a sensor signal from the at least one of the bleed air system sensor to define a sensor output, comparing the sensor output to a reference value, and di...
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JP6042901B2 |
A method for making an acoustic structure that includes a honeycomb having cells in which septum caps are located. The septum caps are formed from sheets of flexible material that may be perforated before or after the material is inserte...
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JP6027193B2 |
A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion se...
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JP2016534276A |
A reverse thrust system (12C) suitable for a high bypass turbofan engine (10) of a type which has Nasser (12) contains advancing-side-by-side Cowl (34A) who has a storing position, a deployment position, and an open position. a hinge ass...
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JP2016531032A |
A method of assembling a turbine engine (10) that rotates a turboprop assembly (18) of an aircraft (30) to help lower the operating temperature of the fluid used is a liquid gas heat exchanger (50, 51). , 52, 150, 152) and the step of ad...
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JP5997508B2 |
A method and system suitable facilitating the connection and disconnection of a thrust reverser assembly to a fan case of a nacelle of a gas turbine engine. The method and system entail operating a clamping system to simultaneously engag...
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JP5996040B2 |
The invention is related to an aircraft 1 with a fuselage 2 that accommodates at least one air breathing propulsion engine 8a, said fuselage 2 having a maximum fuselage width determined in the region of said at least one air breathing pr...
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JP2016121687A |
To improve the engine specific fuel consumption (SFC) for an accessory gearbox drive blower and other similar blowers.A turbine engine system includes an inlet particle separator (36) receiving an inlet fluid flow and having a clean outl...
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JP2016107958A |
To provide a boundary layer controller configured to correspond to the intake side inner peripheral surface shape of a propulsion engine in an aircraft.The boundary layer controller includes a venturi generator 10 configured such that wh...
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JP5932782B2 |
An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of th...
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JP2016102499A |
To solve some problems that since a jet engine has a wide opened air inlet, the jet engine sometimes sucks foreign materials during ground sliding or flight in the air to show a quite dangerous state, due to this state, a fan or an engin...
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JP2016508914A |
According to the present invention, the spacecraft is provided with movable flaps 6 in front of each of the air inlets 5 of the turbo engine 4, the movable flaps 6 having a first position for opening the air inlets 5 and the air being th...
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JP2016506470A |
Thrust system suitable for high bypass turbofan engine and its operation. Thrust reversal systems include a cascade system adapted to translate with the translational cowl in the rear direction of the engine to expose the circumferential...
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JP2016506469A |
A thrust system suitable for a turbofan engine and its operating method. The blocker doors of the thrust system have a containment position where each door is located between the fixed structure of the engine and the translational cowl. ...
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JP5856677B2 |
A honeycomb structure dial includes cells in which septums are located to provide acoustic dampening. The cells are formed by at least our walls wherein at least two of the walls are substantially parallel to each other. The septums incl...
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JP2016009146A |
To provide a technique for manufacturing a sandwich-type sound absorption panel using a fiber-reinforced composite material, which fully or partially abolishes drilling to a skin panel, and dramatically reduces manufacturing costs.In a s...
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JP2016008040A |
To provide a boundary layer control device of an aircraft which suppresses boundary layer separation and, thereby, highly contributes to stable flight of the aircraft even upon landing and taking-off of the aircraft in which the separati...
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JP5822851B2 |
The invention relates to a method of manufacturing a composite acoustic panel employed in an inlet passage of a gas turbine engine (1). The acoustic panel comprises a permeable face-layer (8), an impermeable backing sheet (9) and a sound...
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JP5795708B2 |
A thermally actuated venting system (12) includes a thermally actuated vent (46) for opening a vent outlet (48) in a gas turbine engine (10) associated compartment (11) with a passive thermal actuator (54) located in the compartment (11)...
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JP2015171846A |
To provide an intake lip with radio wave absorption performance by a lightweight and simple configuration.The intake duct includes an intake port provided in an aircraft and opened forward of an airframe. In the intake lip 10 of the inta...
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JP2015168314A |
To provide a missile having intake, in which air pressure does not increase because a front face project area does not increase, and because strong impact wave caused by an intake cover does not occur during boost time, large wave drag d...
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JP5722309B2 |
A brushless starter/generator includes a rotor rotatably mounted within a stator mounted within a housing and an oil cooling system using cooling oil from an engine accessory gearbox for cooling the rotor and the stator. The rotor is fix...
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JP5707367B2 |
A helicopter 10 includes a mast 14, a main rotor 16, an engine 32, a radiator 34 and a body cover 24. The engine 32 and the radiator 34 are housed in the body cover 24. The body cover 24 has an opening 66 penetrated by the mast 14; an op...
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JP5700890B1 |
To freeze water in an aircraft due to a phase change or to attach ice to a member constituting the heat exchanger in an aircraft heat exchanger for heat exchange between aircraft fuel and oil. To prevent. An aviation heat exchanger 3 inc...
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JP5655069B2 |
A method and system for an integrated ejector valve assembly is provided. The integrated ejector valve assembly includes a first valve assembly configured to control a flow of relatively lower pressure fluid from a first inlet port, a se...
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JP2014521118A |
A panel assembly and method of making the same, whereby the panel assembly includes an adhesive located onto one or more edges of a layered honeycomb structure and a mesh material adhered in between the layered honeycomb structure by the...
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JP5577320B2 |
According to the invention, fresh air at the turboprop outlet is captured and mixed with the warm airflow created by said turboprop to lower the temperature, via a device having a tubular sleeve able to slide into the tubular duct while ...
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JP5554030B2 |
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JP5524513B2 |
A helicopter (1) having a drive (6) in turn having an air intake conduit (12); a main rotor (3) connected functionally to the drive (6); and a transmission (9) interposed functionally between the main rotor (3) and the drive (6) and hous...
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JP5510872B2 |
A personal flight device which includes a housing which is securable to a pilot having at least one pair of ducted fans, one fan of the at least one pair of ducted fans is mounted to one side of the housing, the other fan of the at least...
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JP5480888B2 |
Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: • deployment (E3) of the previously armed thrust reversers of the aircraf...
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JP2014070548A |
To provide a reheat device capable of absorbing electromagnetic waves coming from a nozzle while maintaining a flame holding function, and capable of increasing stealthiness against electromagnetic radar detection.A reheating device incl...
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JP5459798B2 |
An acoustic treatment panel includes, from the inside to the outside, a reflective layer (50), at least one alveolar structure (52), and at least one acoustically resistive structure (54) that forms an aerodynamic surface, whereby the pa...
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JP5460952B2 |
An inlet apparatus (10) and method for use with a cabin air compressor on a high speed, airborne mobile platform (12), such as a commercial or military aircraft. The apparatus includes a Pitot inlet (16,102) of a desired shape that is su...
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JP5425908B2 |
An inner wall for a nacelle of a turbomachine, the inner wall including an outer annular fan casing for surrounding the fan blades and including at its upstream end a flange for fastening to a ring in axial alignment therewith, and a sou...
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JP5416786B2 |
An air intake for an aeroplane engine of type with unducted propellers, which intake can be connected by a pylon to a fuselage of an aeroplane, a local length of the air intake, measured parallel to the axis of the engine between a point...
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JP5406251B2 |
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JP5405083B2 |
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JP2013252756A |
To provide a center-of-gravity moving device for a flying object, which minimizes an occupying space of the device while giving shapes and arrangement of constituent elements a large degree of freedom to efficiently utilize a limited spa...
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JP5325411B2 |
An embodiment of the technology described herein is an auxiliary power unit assembly (10). The auxiliary power unit assembly (10) includes an auxiliary power unit being installable in an aircraft (18) having a cabin (22), a duct (28) con...
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JP5265519B2 |
Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the en...
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JP5224607B2 |
The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least o...
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JP2013525196A |
A method of processing acoustic waves emitted at an outlet of a turbo engine of an aircraft with a dielectric barrier discharge device, and an aircraft including such a device. The method includes activating the dielectric barrier discha...
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