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Patent Searching and Data


Matches 301 - 350 out of 1,101

Document Document Title
WO/2007/147965A2
Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment (15) of the anterior part (14) of the fairing (7) for the suspension pylon (6) is radially flexible.  
WO/2007/147965A3
Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment (15) of the anterior part (14) of the fairing (7) for the suspension pylon (6) is radially flexible.  
WO/2007/131979A1
The present invention relates to a device for attaching an aircraft engine comprising a rigid structure forming a box, and a device for taking up the thrust forces having a main brace (34) mounted fixedly on one of the longerons (17) for...  
WO/2007/120199A3
An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a thruster mounted to an aircraft ...  
WO/2007/107647A1
Aircraft having reduced environmental impact. According to the invention, said aircraft comprises at least one engine (10) with at least one propeller (12, 13) carried, at the rear, on the top of said aircraft with the propeller(s) locat...  
WO/2007/104940A1
In an aircraft comprising a payload region (2) and a wing section (21, 31) which carries an engine (24, 33) of a kind which, in use, generates a flow of exhaust gases, the wing section (21, 31) is provided with or has associated therewit...  
WO/2007/051938A2
The invention relates to a front device (100) for fastening a turbojet engine (1) to an aircraft fixing strut (3), which is used for absorbing trust loads of said turbojet engine and is characterised in that it comprises a top bracket (1...  
WO/2007/051938A3
The invention relates to a front device (100) for fastening a turbojet engine (1) to an aircraft fixing strut (3), which is used for absorbing trust loads of said turbojet engine and is characterised in that it comprises a top bracket (1...  
WO/2007/051914A1
Disclosed is an aircraft having a reduced environmental impact. According to the invention, this aircraft comprises at least one engine (7) having at least one propeller (9, 10) supported, at the rear, on the back of the aircraft with th...  
WO/2007/042453A1
The invention concerns a rigid framework (8) for aircraft engine mounting structure, in the form of a structure box closed by first and second structure box side panels (34a, 34b), said framework comprising inter-rib spaces (381 à 388) ...  
WO/2007/042508A1
The invention concerns a nut system (100) comprising a nut (104) provided with a main thread (106) of pitch p1 and arranged along a screwing axis (108) of the nut. The invention is characterized in that it further comprises a threaded me...  
WO/2007/039556A8
The invention concerns a turbojet engine mounting structure for aircraft comprising a central structure box (22) formed by the assembly of two panels joined via transverse ribs (23), the mounting structure further comprising two lateral ...  
WO/2007/039556A1
The invention concerns a turbojet engine mounting structure for aircraft comprising a central structure box (22) formed by the assembly of two panels joined via transverse ribs (23), the mounting structure further comprising two lateral ...  
WO/2007/036521A1
The invention concerns an engine assembly (1) for an aircraft comprising an engine (2) and an engine mounting structure (4), said structure comprising a rigid structure (10) including a structure box (24) and a mounting system (11) inter...  
WO/2007/036527A1
The invention relates to an engine assembly for an aircraft, consisting of a turbojet, a pylon and a plurality of engine mounts, the latter comprising first and second front mounts (6a) which are fixed to the fan case and which are dispo...  
WO/2007/036519A1
The invention concerns an engine mounting structure designed to be interposed between an aircraft wing system and said engine, the structure comprising a rigid structure (8) as well as front aerodynamic structure (24) mounted fixedly on ...  
WO/2007/036516A1
The invention concerns a novel engine mounting structure for coupling an aircraft engine assembly. The engine mounting structure (50) comprises a monolithic framework (20), constructed by smelting or welding for example, covered with mec...  
WO/2007/033995A1
The invention concerns a strut for locking (4) the engine of an aircraft, the strut comprising a rigid structure (10) forming a structure box closed at the front by a front closing rib (36), as well as a system for mounting the engine in...  
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...  

Matches 301 - 350 out of 1,101