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Patent Searching and Data


Matches 301 - 350 out of 1,070

Document Document Title
WO/2007/034094A1
The invention concerns a turbojet (1) for aircraft, characterized in that it supports at least one tail fin (7), said tail fin being fixed on the strong structure (11) of said turbojet so as to form a single-unit assembly. The turbojet m...  
WO/2007/033993A1
The invention concerns a method for mounting an aircraft engine on a rigid structure of a strut, comprising a step of fixing, on the structure a locking body (46) of an engine fastener, said locking body being designed to be pressed agai...  
WO/2007/028764A1
The invention relates to a system (33) for connecting a crossbar to the rigid structure of an aircraft engine pylon, comprising an axle system (32) which is mounted to slide in a first passage (38) in a fitting (34) such that it can move...  
WO/2007/022315A3
An integrated aircraft propulsion system includes a pulse detonation engine integrated with a lifting surface to achieve supercirculation. The exhaust from the pulse detonation engine is expelled in a rearward direction tangentially to t...  
WO/2007/017339A1
The invention relates to a primary engine (9) strut (11) structure of an aircraft characterized in that it comprises single-piece composite panels (1a, 2a, 3a, 4a) while replacing the metallic spars (1, 2) and metal panels (3, 4), said c...  
WO/2007/012667A1
The invention concerns an assembly for aircraft comprising a wing system element (2) as well as an attachment mast, the assembly further comprising means for attaching (8) the mast on the element (2), said means (8) including two front h...  
WO/2007/000546A3
The invention relates to an aircraft engine unit (1) comprising a jet engine (2), a suspension pylon (4) and a plurality of engine fasteners. According to said invention, the plurality of fasteners comprises first (6a) and second (6b) fr...  
WO/2007/000457A1
The invention relates to an engine mounting structure for an aircraft, said structure comprising a rear engine mount (8) which is provided with a rear mount body (54) and a first shear slug (66) that can take over the effort exerted in a...  
WO/2007/000456A1
The invention relates to an engine mounting structure for an aircraft, said structure comprising a rear engine mount (8) provided with a rear mount body (54) and two lateral fittings (26), each comprising a longitudinal part which comes ...  
WO/2007/000546A2
The invention relates to an aircraft engine unit (1) comprising a jet engine (2), a suspension pylon (4) and a plurality of engine fasteners. According to said invention, the plurality of fasteners comprises first (6a) and second (6b) fr...  
WO/2007/000458A1
The invention relates to an engine mount for an aircraft, to be placed between an engine and an engine mounting structure, said mount comprising a shackle (20) which is connected to a first fixing device (34) comprising a fork (36) provi...  
WO/2007/001371A3
A vibration isolation engine mount system and method for ducted fan aircraft, such as ducted fan vertical takeoff and landing (VTOL) aircraft, includes an engine for driving the ducted fan. The system includes an engine support structure...  
WO2006108957A3
The invention concerns an aircraft comprising: a rear vertical tail unit consisting of at least two tail fins (5, 6) forming, with the rear part (7) of said fuselage (4), a channel (8) arranged on the back thereof; and at least one turbi...  
WO/2006/124745A3
A fuel distributor (10) and mounting arrangement that helps support the weight of the fuel distributor (10) during removal and replacement for improved maintainability. The mounting arrangement includes a hanger (60) mountable on a first...  
WO/2006/124745A2
A fuel distributor (10) and mounting arrangement that helps support the weight of the fuel distributor (10) during removal and replacement for improved maintainability. The mounting arrangement includes a hanger (60) mountable on a first...  
WO/2006/113388A3
An engine air particle filter system in a helicopter having a support structure that is fixed to the helicopter. The support structure has a plurality of ribs. The plurality of ribs and the support structure form a plurality of openings....  
WO/2006/108957A2
The invention concerns an aircraft comprising: a rear vertical tail unit consisting of at least two tail fins (5, 6) forming, with the rear part (7) of said fuselage (4), a channel (8) arranged on the back thereof; and at least one turbi...  
WO/2006/108028A2
The invention provides an aircraft with an auxiliary power unit (22) isolated from the aircraft. An auxiliary power unit suspension system (20) includes at least one suspension linkage (32). The suspension linkage terminates with a first...  
WO/2006/108028A3
The invention provides an aircraft with an auxiliary power unit (22) isolated from the aircraft. An auxiliary power unit suspension system (20) includes at least one suspension linkage (32). The suspension linkage terminates with a first...  
WO/2006/103774A1
A flying body comprising a fuselage (100a), a lift engine (102a1), and an attitude control engine. The lift engine comprises a gas production device (200a1) producing a turbine drive gas, first thrust devices (204a1, 208a1, 210a1) obtain...  
WO/2006/100094A1
Modern aircraft carry larger quantities of water. One exemplary embodiment of this invention describes a supply system that encompasses a vapor generator (109) The vapor generator is supplied with hydrogen (104) and oxygen (101-103), and...  
WO/2006/097484A1
The invention concerns an engine fastener of a mounting system designed to be interposed between a rigid structure of an attachment strut of an aircraft engine and engine, the fastener comprising a main body (130), a control bar mounted ...  
WO/2006/093512A1
Methods and apparatuses for controlling airflow proximate to engine/airfoil systems are disclosed. In one embodiment, an aircraft system includes an airfoil and an engine unit at least proximate to the airfoil with a gap between a portio...  
WO/2006/090031A1
The invention relates to an aircraft engine assembly (1) comprising a turbojet (2), a pylon (4) and a plurality of engine mounts (6a, 6b, 8) which are disposed between the pylon (4) and the turbojet (2). According to the invention, each ...  
WO/2006/090032A1
The invention relates to a turbojet pylon for an aircraft, comprising a rigid structure (10) which is equipped with a plurality of half-rings (30) that are arranged such as to define part of an essentially-cylindrical imaginary surface (...  
WO2005121598A3
A transmission system (20) that is used in conjunction with a microturbine engine (12) for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other...  
WO/2006/068600A1
The invention relates to an annular torsional rigid static component for an aircraft engine, the component comprises at least one means (101) for mounting the engine to an aircraft. Said mounting means (101) comprises a body (103) formed...  
WO/2006/062497A1
A tip turbine engine assembly (8) includes a fan (32) rotatable in a fan plane (22) about an engine centerline (112). The fan (32) includes a fan blade (34) that defines a core airflow passage therethrough. An engine case (10) surrounds ...  
WO/2006/059979A1
A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inward...  
WO/2006/056678A1
The inventive fixing system comprises a front attachment (6), a rear attachment (7) and an intermediate attachment (8) connecting a strut (1) to a wing (2), wherein the lower fitting (17) of the rear attachment (7) is fixedly connected t...  
WO/2006/051229A1
The invention relates to a connector assembly (1, 100) for connecting a motor to the cable (5, 103) of a strut fixing said motor to an aircraft wing. A male part (2, 101) comprises pins (7, 107) and female part (3, 102) lugs (10, 108). I...  
WO/2006/042982A1
The invention concerns a vertical tail unit (5) for an aircraft (1). The vertical tail unit is provided with an engine (7). The engine extends cantilevered beyond a fin (11) of the vertical tail unit and is secured to said fin by a mount...  
WO/2006/021721A1
The invention relates to an aircraft engine unit comprising a turboshaft engine, a pylon and a plurality of engine mounts which are disposed between the pylon and the turboshaft engine. According to the invention, the plurality of engine...  
WO/2006/021722A1
The invention concerns an engine assembly (1) for aircraft comprising a turboshaft engine (2), an engine strut suspension (4) as well as a plurality of engine attachments (6a, 6b, 8) interposed between the engine strut suspension (4) and...  
WO2005084156A3
Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft...  
WO/2006/016031A1
The invention relates to a multi-engine aircraft whose at least two engines (2, 3) are fixed to the fuselage wings symmetrically with respect to the longitudinal vertical plane of symmetry thereof, respectively and the third engine (7) i...  
WO/2006/007689A1
An aircraft propulsion system (10) or a fixed wing aircraft (12) having a power plant or gas turbine engine (18) driving a number of outboard propulsion units (20) mounting to pylons (24) extending laterally outwardly from the fuselage (...  
WO2003057331A3
The present invention in one embodiment includes an aircraft having a fuselage with a powered propeller. The aircraft further includes a cambered main wing positioned aft of the fuselage and has a non cambered portion connected to the fu...  
WO2005047102A3
An aircraft (400) for low sonic boom supersonic flight conditions includes a wing (404) with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to accoun...  
WO2004100289A8
A neutral buoyant airship, such as a blimp, contains a lifting body which allows the airship to remain neutrally buoyant in air and fuel cell located in the airship. A method of generating power in the neutrally buoyant airship, comprisi...  
WO2004100289A3  
WO2004065208A3
A VTOL aircraft with magnetic linear induction powered impeller rotors (21b). The craft may have many configurations of multiple or single rotors. Directional control is included through the use of vanes or thrust tilting of the rotors.  
WO/2005/084156A2
Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft...  
WO/2005/075842A1
The invention concerns an articulated junction device (1) arranged between a first structure (2) and a second structure (4), the device being adapted to ensure transmission, from one structure to the other, of a single load oriented alon...  
WO/2005/070763A1
[PROBLEMS] To provide a rotor with a shroud operated on the driving principle of a linear motor stably rotatable even if the rotor is increased in size and used horizontally or the blowing direction thereof is rapidly changed. [MEANS FOR...  
WO2005003324A3
A VTOL vehicle including a fuselage with two foldable wings, two tiltable nacelles attached to the wings, a vertical stabilizer, a horizontal stabilizer, and two auxiliary thrusters. Each nacelle contains a system of vanes located at the...  
WO/2005/047103A1
A glide kite airplane capable of a variable speed flight to enable a safe flight and take-off and landing and allow incidental facilities to be made on a small scale in that propulsion air currents from a propelling device are used for b...  
WO/2005/047102A2
An aircraft (400) for low sonic boom supersonic flight conditions includes a wing (404) with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to accoun...  
WO/2005/035362A1
For a transport of a cargo within the earth atmosphere and into the space and back there is designed a cargo transport means provided with transfer means for movement up to the height of about 80 km above the earth surface and transporta...  
WO2005014391A8
The invention relates to multipurpose heavier-than-air aircrafts which can be used in the form of an airplane, helicopter or a sailplane. The inventive multipurpose heavier-than-air aircraft consists of a body comprising a tail assembly ...  

Matches 301 - 350 out of 1,070