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Matches 301 - 350 out of 1,461

Document Document Title
WO/2011/037850A2
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...  
WO/2011/037855A2
An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes co...  
WO/2011/036386A1
The invention relates to an engine (22) attached to an engine pylon (23, 24) via an intermediate structure (39) assembled by flanges (40, 41), to the pylon and to the engine, a rigid structure (42) connecting the flanges. Said arrangemen...  
WO/2011/037850A3
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...  
WO/2011/023396A2
The invention relates to an aircraft having a wing and a fuselage carrying one or several fins (502, 503) at a rear portion thereof. The aircraft has several electrical propulsion groups (510, 520, 530, 540) being directly carried by sai...  
WO/2011/023396A3
The invention relates to an aircraft having a wing and a fuselage carrying one or several fins (502, 503) at a rear portion thereof. The aircraft has several electrical propulsion groups (510, 520, 530, 540) being directly carried by sai...  
WO/2011/012821A3
The present invention relates to an assembly for an aircraft comprising means (54) for attaching a primary structure (46) of an attachment strut to a wing (6), forming an isostatic system and comprising in particular: an attachment (102)...  
WO/2011/012821A2
The present invention relates to an assembly for an aircraft comprising means (54) for attaching a primary structure (46) of an attachment strut to a wing (6), forming an isostatic system and comprising in particular: an attachment (102)...  
WO/2011/012822A2
The present invention relates to an engine assembly (1) for an aircraft comprising a dual-flow turbine engine (2) and an attachment strut (4), the turbine engine comprising a structural case (40) extending downstream from the hub (20) of...  
WO/2011/012603A2
The invention relates to a beam (11) for suspending a turboshaft engine from an aircraft structure, comprising a first attachment means (12) intended to be secured to the aircraft structure and at least one second attachment means (13, 1...  
WO/2011/012822A3
The present invention relates to an engine assembly (1) for an aircraft comprising a dual-flow turbine engine (2) and an attachment strut (4), the turbine engine comprising a structural case (40) extending downstream from the hub (20) of...  
WO/2011/012603A3
The invention relates to a beam (11) for suspending a turboshaft engine from an aircraft structure, comprising a first attachment means (12) intended to be secured to the aircraft structure and at least one second attachment means (13, 1...  
WO/2011/001121A1
The invention relates to a system for attaching an element (3) capable of vibrating onto an aircraft structure (2), comprising at least one pair of scoops (10) attached onto the element capable of vibrating, as well as onto the structure...  
WO/2010/140082A9
A UAV with an engine (34) attached to rear (38) of its fuselage by an engine mounting assembly with the rotational axis of the engine generally parallel with the axis (45) of the fuselage. The engine mounting assembly includes a fuselage...  
WO/2010/140082A1
A UAV with an engine (34) attached to rear (38) of its fuselage by an engine mounting assembly with the rotational axis of the engine generally parallel with the axis (45) of the fuselage. The engine mounting assembly includes a fuselage...  
WO/2010/129210A3
A bidirectional flying wing maximizes efficiency and reduces sonic boom during supersonic flight. The flying wing has bilateral symmetry across two perpendicular planes and a substantially isentropic compression bottom surface that minim...  
WO/2010/129210A2
A bidirectional flying wing maximizes efficiency and reduces sonic boom during supersonic flight. The flying wing has bilateral symmetry across two perpendicular planes and a substantially isentropic compression bottom surface that minim...  
WO/2010/111800A1
The invention relates to an ultralight electric motor-driven aircraft (10) comprising a rigid supporting structure (11) provided with a harness (20) for a pilot (9) and a sail (13) from which the supporting structure is suspended. A prop...  
WO/2010/112742A2
The invention relates to a rear section of an aircraft including two connecting rods (66) symmetrically arranged on either side of a vertical median plane (P), each connecting rod having an end mounted on an engine mounting structure (14...  
WO/2010/112742A3
The invention relates to a rear section of an aircraft including two connecting rods (66) symmetrically arranged on either side of a vertical median plane (P), each connecting rod having an end mounted on an engine mounting structure (14...  
WO/2010/106343A3
An electric and hybrid Vertical -Take Off and Landing ("VTOL") aircraft is disclosed comprising a plurality of small Electric Ducted Fans ("EDFs") (201-208, 232-235) of various sizes and orientations. The thrust of each fixed EDF (201-20...  
WO/2010/103252A1
The invention relates to an airplane (1), comprising a fuselage (2) having an elongate shape along a longitudinal axis X of the airplane, and at least one wing (3) attached to the fuselage between a front end and a back end (25) of the f...  
WO/2010/094878A3
The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling...  
WO/2010/094878A2
The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling...  
WO/2010/089487A1
The invention relates to a suspension assembly for an aircraft turbojet engine (3), including a pylon (1) and connecting rods (13a, 13b) for taking up the thrust of the turbojet engine (3) and connected to the pylon (1), remarkable in th...  
WO/2010/085360A3
In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine en...  
WO/2010/085360A2
In an embodiment the invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end and...  
WO/2010/079294A1
The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (1a) comprises a means for shifting the axis (la-la) of the blower (9a) transverse to the axis (L...  
WO/2010/066985A1
The invention relates to a system for attaching two components together, such as an aircraft engine and the mounting pylon thereof. According to the invention, at least two of the front (10) or rear (11) trunnions of the attaching system...  
WO/2010/063926A1
The invention relates to a rear aircraft portion (100) including at least one engine assembly having a built-in turbine engine (10), as well as a mounting pylon (14) for mounting the turbine engine. According to the invention, the rigid ...  
WO/2010/063925A1
The invention relates to an aircraft engine assembly (1) that includes a rigid structure (16) provided with a box rib extension (62) protruding from a box (50b) of said structure (16) in a spreading direction (52) towards the aircraft fu...  
WO/2010/063927A1
The invention relates to an aircraft engine assembly (1) including: a mounting pylon that comprises a rigid structure (16) provided with a central box-type structure (24), as well as a front extension (26) and a rear extension (28), eac...  
WO/2010/061070A1
The invention relates to a flying wing (3) that comprises two side wings (5, 7), a central body (9), and at least one propulsion assembly (20) including a turbojet engine (21) surrounded by a nacelle (23), characterised in that the propu...  
WO/2010/061071A3
The invention relates to a nacelle (23) for a turbojet engine (21), comprising an air intake structure (25) capable of directing an air flow towards a fan (27) of a turbojet engine (21), a middle structure (29) for surrounding said fan (...  
WO/2010/061071A2
The invention relates to a nacelle (23) for a turbojet engine (21), comprising an air intake structure (25) capable of directing an air flow towards a fan (27) of a turbojet engine (21), a middle structure (29) for surrounding said fan (...  
WO/2010/059303A1
A payload or cargo is delivered from a cargo hold of an aircraft during flight, by orienting the fuselage into a nose-up and tail-down position of at least 30 degrees off horizontal, and lowering the cargo from a cargo hold in the fusela...  
WO/2010/059303A4
A payload or cargo is delivered from a cargo hold of an aircraft during flight, by orienting the fuselage into a nose-up and tail-down position of at least 30 degrees off horizontal, and lowering the cargo from a cargo hold in the fusela...  
WO/2010/055224A1
Air intake (113) for an aeroplane engine of the type with unducted propellers, which intake is intended to be connected by a pylon (134) to the fuselage of an aeroplane, the local length of this air intake, measured parallel to the axis ...  
WO/2010/046938A1
The present invention comprises a device to generate the thrust of an aircraft in general, as for example airplanes or helicopters, and comprising means (1) operatively connected to at least a propeller (2) that generates the thrust. Acc...  
WO/2010/041098A1
Constitutes a real technological alternative of innovation and application because it does not require the use of fossil fuels. On the contrary, this invention uses clean, renewable and environmentally-friendly energy. Wind-powered aerop...  
WO/2010/037917A1
This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a w...  
WO/2010/031958A3
The invention relates to a rear part of an aircraft (1), comprising a structure for supporting engines (14), extending through the fuselage (6), through two openings (18, 18) distributed either side of a vertical median plane (P) of the ...  
WO/2010/031960A1
The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), passing through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means co...  
WO/2010/031958A2
The invention relates to a rear part of an aircraft (1), comprising a structure for supporting engines (14), extending through the fuselage (6), through two openings (18, 18) distributed either side of a vertical median plane (P) of the ...  
WO/2010/031959A1
The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), extending through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means ...  
WO/2010/024736A1
The invention comprises a component with a first member (12), a second member (17) and a device (100) for fastening the first member (12) to the second member (17). A first hole (101) extends through a portion of the first member (12) an...  
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 ...  

Matches 301 - 350 out of 1,461