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Patent Searching and Data


Matches 301 - 350 out of 1,312

Document Document Title
WO/2010/020199A1
The invention relates to the aircraft hybrid propulsion, consisting of two propeller propulsion units, one of which is based on the principle of an internal combustion engine (1). with a propeller and the second one on the principle of a...  
WO/2010/022362A2
A first trailing edge portion (26) of a scarfed jet engine exhaust nozzle (24) aft of a second trailing edge portion (30) relative to a central axis (16) of an associated exhaust duct (10, 10.1) causes an automatic nozzle-pressure-ratio ...  
WO/2010/018323A1
The invention relates to an engine pylon for an aircraft that comprises a primary structure including aircraft mounting points arranged symmetrically relative to a middle vertical longitudinal plane of the pylon, characterised in that th...  
WO/2010/010293A2
The aircraft (50) of the invention includes at least one engine (56) having counter-rotating rotors (58a, 58b), the engine or at least one of the engines having imbalances associated with at least one ellipse (70). The aircraft includes ...  
WO/2010/009708A1
The invention relates to an engine comprising a core engine and at least one thruster disposed separately from the core engine. The core engine thereby comprises a compressor stage (1, 2), a high-pressure combustion chamber (3), and a hi...  
WO/2010/007226A3
Aircraft propulsion system (10) comprising a bypass turbojet engine which is surrounded by a nacelle, and means (80) of attaching the engine to a pylon (16) of an aircraft, the nacelle (12) comprising an internal structure exhibiting sym...  
WO/2010/007226A2
Aircraft propulsion system (10) comprising a bypass turbojet engine which is surrounded by a nacelle, and means (80) of attaching the engine to a pylon (16) of an aircraft, the nacelle (12) comprising an internal structure exhibiting sym...  
WO/2010/003698A1
Aircraft (1) comprising a fuselage (3) and two aerodynamic wings with at least two respective propeller drives (11, 12, 13, 14) disposed thereon at a distance from one another in the span width direction of the wings, each of said propel...  
WO/2009/153471A2
The invention relates to an aircraft powered by hybrid power that comprises: an outer structure (12 to 20); electric equipment (34); internal combustion propulsion means (40); and a means for supplying power to the propulsion means; char...  
WO/2009/153471A3
The invention relates to an aircraft powered by hybrid power that comprises: an outer structure (12 to 20); electric equipment (34); internal combustion propulsion means (40); and a means for supplying power to the propulsion means; char...  
WO/2009/151622A1
Thrust systems for passenger aircraft provide at least one flight engine (66) and a taxi engine (70) wherein all' flight engines together provide, in total, a takeoff thrust (65) arranged in a takeoff thrust direction and the taxi engine...  
WO/2009/147342A2
The invention relates to a mounting pylon for an aircraft engine that comprises a rigid structure (10) provided with a box (24) formed by one or more hollow segments (28, 30, 32). According to the invention, at least one hollow segment h...  
WO/2009/147341A2
The invention relates to a mounting pylon for the engine of an aircraft that comprises a rigid structure provided with a box (24) formed by an upper spar (26) and a lower spar (28) connected together by two side panels (30). At least one...  
WO/2009/147342A3
The invention relates to a mounting pylon for an aircraft engine that comprises a rigid structure (10) provided with a box (24) formed by one or more hollow segments (28, 30, 32). According to the invention, at least one hollow segment h...  
WO/2009/147341A3
The invention relates to a mounting pylon for the engine of an aircraft that comprises a rigid structure provided with a box (24) formed by an upper spar (26) and a lower spar (28) connected together by two side panels (30). At least one...  
WO/2009/132846A2
The invention relates to an aircraft which comprises: a fuselage having a fuselage part (1), a power supply device (E), and at least two receiving devices (A) on the fuselage part (1) for fastening the power supply device (E). The invent...  
WO/2009/132846A3
The invention relates to an aircraft which comprises: a fuselage having a fuselage part (1), a power supply device (E), and at least two receiving devices (A) on the fuselage part (1) for fastening the power supply device (E). The invent...  
WO/2009/118469A3
The invention relates to an effort recovery structure (101) of a connecting strut for attaching a turboreactor to the wing system of an aircraft. Said structure comprises a first lateral block (102) and a second lateral block (103) to be...  
WO/2009/118469A2
The invention relates to an effort recovery structure (101) of a connecting strut for attaching a turboreactor to the wing system of an aircraft. Said structure comprises a first lateral block (102) and a second lateral block (103) to be...  
WO/2009/114916A1
Engine-propeller driving system comprising a device to transmit the power generated by an engine (5) to a propeller comprising an aircraft / vehicle (2) fuselage structure (1 ) that passes inside the propeller hub (3) so that the fuselag...  
WO/2009/112777A2
The invention relates to an aircraft engine assembly comprising means for mounting a turbojet (2) on a rigid mounting strut structure, these means comprising first, second and third thrust load-absorbing front engine mounts (6a, 6b, 8) f...  
WO/2009/112777A3
The invention relates to an aircraft engine assembly comprising means for mounting a turbojet (2) on a rigid mounting strut structure, these means comprising first, second and third thrust load-absorbing front engine mounts (6a, 6b, 8) f...  
WO/2009/112782A2
The invention relates to an aircraft engine assembly comprising an annular structure (60) surrounding a central casing (16) and mechanically connected thereto by mounting means (62). Associated with each of the said first and second engi...  
WO/2009/112781A3
The invention relates to an aircraft engine assembly comprising an annular load-transfer structure surrounding the central casing (16) and connected to a plurality of substantially planar structures arranged externally with respect to th...  
WO/2009/112782A3
The invention relates to an aircraft engine assembly comprising an annular structure (60) surrounding a central casing (16) and mechanically connected thereto by mounting means (62). Associated with each of the said first and second engi...  
WO/2009/112669A1
The present invention relates to an attachment structure (1) for attaching a turbojet engine (2) to a fixed structure of an airplane via an attachment pylon, characterized in that it comprises a one-piece box section intended to extend a...  
WO/2009/112781A2
The invention relates to an aircraft engine assembly comprising an annular load-transfer structure surrounding the central casing (16) and connected to a plurality of substantially planar structures arranged externally with respect to th...  
WO/2009/097668A2
Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air...  
WO/2009/095257A2
Wing-propulsion unit combination comprising a wing (W) with a main wing (W1) and a propulsion unit (E) with a pre-mix chamber (E1), a combustion chamber and a hot air chamber (E2), further comprising: a) a propulsion unit tap air channel...  
WO/2009/083073A3
A fuel cell system module (10) for use in an aircraft (32) comprises at least one fuel cell system component (12, 22, 24). The fuel cell system module (10) can be connected in a modular manner to a fuselage section (30) of the aircraft (...  
WO/2009/080732A3
The invention relates to a configuration of engines (3) for aircraft located in the rear part of the fuselage (2) of said aircraft, the engines (3) being attached in a fixed manner by pylons (5) to the structure of the aircraft, said str...  
WO/2009/080732A2
The invention relates to a configuration of engines (3) for aircraft located in the rear part of the fuselage (2) of said aircraft, the engines (3) being attached in a fixed manner by pylons (5) to the structure of the aircraft, said str...  
WO/2009/068638A1
The invention relates to a structural configuration of the rear fuselage (4) of an aircraft with propeller engines (1) comprising propellers (23) formed in turn by blades (3), the mentioned propeller engines (1) being located at the rear...  
WO/2009/066103A1
An aircraft engine mounting structure comprising a pylon box having an upper surface and at least one attachment element configured to be attached to a front spar of an aircraft wing box, the front spar having a lower surface, the attach...  
WO/2009/060138A3
The invention relates to a propulsion assembly for an aircraft, that comprises : a turbojet engine (1) including a fan casing (3) and an engine casing (5) ; a pylon for holding said turbojet engine (1); and a device for suspending said t...  
WO/2009/060138A2
The invention relates to a propulsion assembly for an aircraft, that comprises : a turbojet engine (1) including a fan casing (3) and an engine casing (5) ; a pylon for holding said turbojet engine (1); and a device for suspending said t...  
WO/2009/053560A2
The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of...  
WO/2009/053560A3
The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of...  
WO/2009/053560A8
The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of...  
WO/2009/048713A1
A heat shield (2) includes a ceramic composite heat shield panel (3) having a generally concave first surface and a generally convex second surface and a pair of thickened panel edge portions (9) provided in the heat shield panel. A heat...  
WO/2009/043924A1
Arrangement for mounting a propulsive system on an aircraft airframe (12) by means of an external strut (4) which connects the engine (1) with the airframe (12), said strut (4) comprising a plurality of spars (8) intruding into the airfr...  
WO/2009/036465A9
A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a...  
WO/2009/036465A1
A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a...  
WO/2009/027333A1
The invention mainly relates to a device for attaching an aircraft engine that comprises a rigid structure (10) and a means for attaching the engine on said rigid structure, said attachment means including a rear engine fastener (8) and ...  
WO/2009/027336A1
The invention relates to an engine assembly for an aircraft, that comprises an engine, a device for attaching the engine (4) and a nacelle surrounding the engine and provided with fan coils (34) the attachment device (4) including a rigi...  
WO/2009/007562A1
Steel characterized in that its composition is, in percentages by weight: - C = 0.20 - 0.30%; - Co = traces - 1%; - Cr = 2 - 5%; - Al = 1 - 2%; - Mo + W/2 = 1 - 4%; - V = traces - 0.3%; - Nb = traces - 0.1%; - B = traces - 30 ppm; - Ni =...  
WO/2009/007354A1
The invention relates to an aircraft engine attachment pylon comprising a system for mounting the engine (11) including a device (9) for reacting thrust forces which is equipped with two lateral link rods (90) and with a spreader beam (9...  
WO/2009/007520A3
The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing...  
WO/2009/007520A2
The invention relates to a securing plate (1) for removably securing a one-piece propulsion unit (17) to a wing of an aircraft, characterised in that it includes first connection means (4, 5, 8, 13, 14) for securing the plate to the wing...  
WO/2008/155497A1
The invention relates to a securing mast (100) for securing an engine (1) to the wing (3) of an aircraft, wherein the device includes two fasteners (101, 102), a first end (110, 112) of each fastener being secured to the engine and the s...  

Matches 301 - 350 out of 1,312