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WO/2011/069887A2 |
The invention relates to a high-lift system for an aircraft, comprising a lift flap (4) disposed on an airfoil (2), said lift flap being coupled to the airfoil (2) and designed to be displaceable relative to the airfoil (2) between a ret...
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WO/2011/066031A2 |
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-ho...
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WO/2011/054047A1 |
A compound motion structure (3) for connection between two surfaces comprising a first arm (5) and a second arm (7) swingable coupled together through a first hinge connection ( 13), a first surface (35) coupled to an opposite end of the...
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WO/2011/054532A2 |
A wing (10a) of an aircraft provided with a main wing (10) and an arrangement of leading edge lifting bodies (13a), which as seen with reference to the incident flow direction (F) are arranged on the leading edge, which are adjustably ar...
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WO/2011/026639A1 |
The invention relates to an adjusting mechanism (M) for kinematically guiding an adjusting body (K) during an adjustment of said mobile body on a supporting structure, said adjusting body (K) can be displaced between a retracted position...
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WO/2011/022179A2 |
A method of providing conditional electrical isolation for a bearing is disclosed. An inner race coupled to a first structure and an outer race coupled to a second structure are provided. An isolative means is provided for conditionally ...
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WO/2011/020593A2 |
The invention relates to an adjustment mechanism (10a, 10b) of an adjustment device for coupling an adjustment flap (K) to a main wing (H) of an aerofoil (T) and for adjusting the adjustment flap (K), the adjustment mechanism (10a, 10b) ...
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WO/2011/007759A1 |
Disclosed are a high-lift-generating device, a wing, and a noise-reduction device for the high-lift-generating device, which aim to reduce noise generated when flaps are deployed, suppress degradation of aerodynamic characteristics when ...
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WO/2010/133789A1 |
The invention comprises varying the ratio between the control surface local chord (I) and the vertical stabilizer local chord (L) along the height of the vertical tail (2) in order to adapt the local value of the coefficient of the side ...
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WO/2010/119280A1 |
The present invention provides a panel device for modifying airflow about a wing (110) of an aircraft (120). The panel device may be used to provide a flap (100) or a leading edge slat. The panel device comprises a plurality of independe...
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WO/2010/115815A2 |
The invention relates to a wing of an aircraft or spacecraft, the wing (12) having at least one mobile flow body (10). The wing comprises a mobile supporting device (22) (10) which is connected to the flow body (10) to rotate the flow bo...
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WO/2010/108698A1 |
The invention relates to an aerofoil (T) comprising a main wing and a high lift flap (K) which is movably mounted on the aerofoil (T) by means of at least two adjusting mechanisms (10a, 10b) that are located next to one another in the di...
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WO/2010/108699A1 |
The invention relates to an aerofoil (T) comprising a main wing and a high lift flap (K) which is movably mounted on the aerofoil (T) by means of at least two adjusting mechanisms (1, 2) that are located next to one another in the direct...
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WO/2010/105818A2 |
An aircraft comprising a device for influencing the directional stability of the aircraft, which aircraft comprises: a main wing with ailerons and spoilers, an elevator tailplane comprising an elevator and a vertical tail unit with a rud...
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WO/2010/103157A1 |
The system includes deflection transmission means (16) to provide a deflection position of a moveable flap (8), installed on a mobile HTP (2) of an aircraft (1), for each position of the setting angle of the HTP (2). Preferably, the mean...
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WO/2010/094952A1 |
An aircraft wing load alleviation system incorporating a wing, a spoiler panel (14), a device (16, 17) which restricts circulation of air around a trailing edge of the spoiler and a control system. The spoiler panel is pivotally attached...
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WO/2010/070185A2 |
The invention relates to the trailing edge (3) of an aircraft stabiliser (1) which is made from a composite material and includes an outer skin (40) and an inner skin (41) which are joined to the trailing edge (3) by means of clip-type c...
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WO/2010/070173A2 |
A lifting or stabilising component (11) for an aircraft comprising in the area of its trailing edge a rotary control element (13) rotating around an axis (61) with at least one slot (21) between the tip (15) of the component (11) and the...
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WO/2010/063868A2 |
Aircraft directional control and stabilizing surface, said surface comprising a vertical stabilizer (2) and a rudder (3), it being possible for the aforesaid rudder (3) to be deflected with respect to the vertical stabilizer (2), the rud...
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WO/2010/061020A1 |
This relates to the assembly between a front trimming fitting and the tension joint of the two lateral boxes of the horizontal stabiliser of an aeroplane that comprises a front trimming fitting (1, 1a and 1b), a front shear plate (2), a ...
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WO/2010/052022A2 |
The invention relates to a vane having a regulating flap (1) that can be moved between a retracted position and an extended position and a gap covering device (10) having an adjusting lever (13) and a gap covering flap (11) arranged ther...
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WO/2010/049570A2 |
Fitting for trimming the horizontal stabiliser of an aircraft, made of composite material, said fitting (30) comprising side walls (2a and 2b) of a torsion box, as well as joining means (3a, 3b) that join the fitting (30) to the frames o...
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WO/2010/040501A2 |
The invention relates to a fore flap disposed on the wing of an aircraft, wherein the wing comprises a main wing (24) having an upper planking (21), a lower planking (22), and a profile nose (23), and the fore flap (12) is on the front s...
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WO/2010/040828A1 |
An aircraft (1) has a brake flap (6) arranged upstream of a vertical tail (4), which brake flap (6) can be pivoted out into the air flow approaching the vertical tail (4). To reduce dynamic structural loading of the vertical tail (4), th...
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WO/2010/026410A2 |
A slat support assembly is disclosed. It comprises a slat support arm having a plurality of bearing surfaces extending along its length, the slat support arm being movable to deploy a slat attached to one end of said slat support arm fro...
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WO/2010/022710A2 |
The invention relates to an air brake for an aircraft, in the form of a flap (1) which can be extended into the air stream in order to increase the flow resistance of the air, wherein an extension (4) is provided on the upper side of the...
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WO/2010/017397A1 |
A torque resisting device for a helicopter which comprises a body, a first rotor and a tail rotor wherein the device comprises a deflector secured to and moveable relative to the body, wherein the deflector is positioned between the main...
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WO/2010/010217A2 |
The invention relates to an aircraft control surface (1), in particular for an aircraft supporting surface (2), comprising a primary control surface (6) including a hinge pin (10) and a secondary control surface (7) including a hinge pin...
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WO/2009/157781A1 |
A personal flight device including : a housing securable to the pilot; at least one pair of ducted fans, one fan of each pair mounted to each side of the housing; wherein each fan rotates about an axis of rotation to draw air through the...
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WO/2009/150445A1 |
A support assembly (1) for guiding a flap (42) on an aircraft wing (41) during deployment of the flap is disclosed. The assembly comprises a guide track (2) defining a two-dimensional path, a cylindrical bearing follower (12) having a lo...
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WO/2009/150446A1 |
A method of operating an aircraft wing assembly, the assembly comprising a main wing element (1) with a leading edge (2); a slat (3) on the leading edge of the main wing element; and a seal member (4). The assembly is placed in a first c...
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WO/2009/148663A1 |
Substantial reduction in aircraft stowage space can be achieved by stacking aircraft using minimal or no folding of parts of the aircraft. This results in reduced complexity and reduced cost compared to other aircraft compact stowage sch...
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WO/2009/136949A1 |
Aircraft fillet fairings with fixed and moveable portions, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing (10) having an upper surface (111), an inboard portion, and ...
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WO/2009/136187A1 |
An aircraft wing assembly comprising: a wing (1); a spoiler (2) pivotally attached to the wing; and a spoiler deployment mechanism. The deployment mechanism comprises a scissor linkage mechanism (7) comprising an upper link (9) pivotally...
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WO/2009/130026A2 |
The invention relates to an aerodynamic body which can be adjusted relative to a main wing of an aircraft by means of an adjusting device, a variable gap (G) being produced on a lateral end (E1, E2) due to the adjustment of the same betw...
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WO/2009/130025A1 |
A lateral coupling device (L) for holding and guiding at least one aerodynamic body in relation to the main wing in the span direction (S) thereof when the latter is adjusted comprises the following: a coupling link (L3), a first couplin...
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WO/2009/124728A2 |
Disclosed is a flow element (1) comprising an external side (3) that has a top face (3a) and a bottom face (3b) in relation to the direction of flow, and lateral end sections (5a, 5b) that form the lateral ends of the flow element (1) tr...
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WO/2009/126905A1 |
An aircraft is equipped with hingeless rotors on tilting nacelles, and the tilt angles of the nacelles are controlled using either or both of an actuator and a mast moment generated by a hingeless rotor. An aircraft with two or more roto...
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WO/2009/124025A1 |
A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward ...
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WO/2009/118547A2 |
An aircraft slat deployment mechanism comprising: a first drive member (4) coupled to the slat at a first pivot point (5); and a second drive member (6) coupled to the slat at a second pivot point (7) which is offset from the first pivot...
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WO/2009/112735A1 |
The invention relates to a panel pivoting about an axis parallel to a side of the panel, which comprises a first continuous coating (1), a main structural frame of a composite stiffener (2, 3, 4, 5, 6) connected to the coating (1) and in...
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WO/2009/101461A1 |
A slat (7) for fixed-wing aircraft that includes a leading edge (3), a trailing edge (5), a chord (C), and an inboard edge (6) that includes particular dimensions (C1, delta) to affect airflow over the wing (2).
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WO/2009/095707A2 |
An aircraft structure comprising: a main structure element comprising a rear spar (10, 11, 12), a control device(15) comprising an control device spar (16, 17, 18), and a hinge assembly comprising: a spar bracket(21) attached to the rear...
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WO/2009/083255A1 |
High lift system for an aircraft having a main wing (1), an uplift flap (2) arranged on the main wing (1) of the aircraft, which can be adjusted by means of a flap-adjusting mechanism for coupling the uplift flap (2) to the main wing (1)...
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WO/2009/080355A2 |
The invention relates to a lift system for an aircraft, comprising a main wing and a slat that can be adjusted in relation to said main wing, into various adjustable states, by means of an adjusting device thus forming a gap (5) between ...
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WO/2009/080736A1 |
The invention relates to a control surface (3) for an aerodynamic lifting surface (2) of aircraft comprising a main closing rib (9) located at one end of the control surface (3) to which a main torsion bar (8) is joined, the mentioned to...
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WO/2009/075963A2 |
Trailing edge device catchers and associated system and method are disclosed xn the form of a redundant mounting system and method. A system in accordance with one embodiment includes a wing having a wmg support (214,217,218), a trailing...
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WO/2009/065597A1 |
The invention relates to a device for moving a trailing edge flap (10) on an aircraft wing (2), wherein the trailing edge flap comprises one or more flap segments (4, 6, 8), a first flap segment (4) being movably mounted on the wing (2) ...
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WO/2009/067319A2 |
A multi- segment flap fence (106) is incorporated into the wing such that a lower fence structure (202) is attached to the underside of the fixed wing (102), an upper fence structure '(212) is attached to the main flap (108) (e.g., at th...
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WO/2009/058488A1 |
Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling (102) extends outwardly from the surface of the airfoil that has an exit plane (202) configured fo...
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