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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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WO/2009/056873A1 |
An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a...
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WO/2009/053649A1 |
The invention relates to a method and a device for creating a continuous protected space along the path of an aircraft (1), in which protected space a maximum induced speed Vtc in a vortex (3) of radius Rtc in the wake of an aircraft (1)...
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WO/2009/040102A1 |
The invention relates to the automatic control of a system of high lift elements (21, 22) of an aircraft, which can be adjusted into a retracted and several extracted configuration for travel flight, holding flight, takeoff or landing, c...
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WO/2009/029306A2 |
Aerospace vehicle fairing systems and associated methods, including fairings (120) that house flap surface drive mechanisms (115) on aircraft, are disclosed herein. A method in accordance with one embodiment, for example, can include adj...
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WO/2009/023340A2 |
Systems and methods for providing supplemental drag to an aircraft are disclosed. In one embodiment, a method includes detecting changes in at least one throttle resolver angle (TRA). Deflections are determined for one or more flight con...
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WO/2009/020452A1 |
A fault-tolerant actuator assembly (20) is mounted on a support (21) for controllably moving a member (22) relative to the support. The actuator assembly includes a first actuator(24) having a first end connected to the support and havin...
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WO/2009/019011A2 |
The invention relates to a high lift system for an aircraft, comprising a main wing (1), a flap (2) disposed on the main wing (1) of the aircraft that can be adjusted between a retracted position and several extended positions relative t...
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WO/2009/017896A2 |
In one embodiment, an apparatus is provided for covering and uncovering a flap opening (14) in an aircraft. The apparatus comprises a door member (22), a torque tube roller member (26), at least one roller member (28), and a biasing memb...
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WO/2009/010431A1 |
The invention relates to an aircraft wing comprising a fixed wing central body and a leading edge mobile flap shutter (16) intended to be rotated with respect to the fixed body in a circular path that lies within a sphere of centre (C). ...
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WO/2009/002206A1 |
The invention relates to aircraft control units. The inventive feathering control surface comprises a device which is used for producing action on the control surface and is freely rotatable about of a main axle attaching the control sur...
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WO2008129074B1 |
The invention provides an aircraft, comprising a fuselage (8), an airfoil (1) mounted to the fuselage (8) and a flap (2; 3) for steering the aircraft. Furthermore, connecting means (18; 79) articularly connect the flap (2; 3) to the airf...
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WO/2008/151760A1 |
A lifting wing (1) has a low pressure side (4), a rear edge (3) and at least one spoiler (8) arranged in the vicinity of the rear edge (3), wherein the spoiler (8) is adjustable in flight to counter an (11) over the low pressure side (4)...
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WO/2008/146656A1 |
A high lift generator which can suppress generation of aerodynamic noise while suppressing increase in body weight. A wing and a noise reduction structure of high lift generator are also provided. The high lift generator comprises a slat...
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WO/2008/147450A1 |
A self-lubricated actuator for a rotor blade flap of a helicopter having a housing; a motor having a shaft disposed in a bearing is provided. The actuator further has an output rod and a mechanism operatively associated with the motor an...
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WO/2008/141618A2 |
The invention relates to a method and a device for flow control on a high lift system on the airfoil of an aircraft, comprising a main profiled body (1) and at least one high lift flap (2) arranged on the main profiled body (1) and confi...
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WO/2008/141622A2 |
The invention relates to a method and a device for flow control on a high lift system on the airfoil of an aircraft, comprising a main profiled body (1) and at least one high lift flap (2; 3) arranged on the main profiled body (1) and co...
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WO/2008/135266A1 |
A high- lift system on the airfoil of an aircraft, comprising a main wing (H) which has a curved main wing nose (N) and comprising a leading-edge flap (V) is disposed re tractably on the main wing (H) by means of an arrangement of severa...
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WO/2008/134193A1 |
A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence (406) during landing and/or other operating conditions, and stow the flap edge fence during othe...
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WO/2008/127482A2 |
An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the s...
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WO/2008/124901A2 |
Flap side edge noise mechanisms have been addressed in a large number of studies during the last decades. A specific vortex system emanates from the flap side edge due to the static pressure difference between the upper and lower flap su...
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WO/2008/127854A2 |
The movable surfaces (403) affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic a...
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WO/2008/123789A1 |
The inventive feathering control surface relates to aircraft engineering, in particular to aircraft control means and can be used for designing pilot-controlled and pilotless airborne vehicles of any type and size provided with adjustabl...
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WO/2008/110521A1 |
A wing (1), comprising a structure, an outer skin (16), and a leading edge device (5) comprising a moveable body (6) with a leading and a trailing edge (15) and a support and actuation mechanism for attaching said moveable body (6) to a ...
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WO/2008/108881A2 |
This patent provides for a method and apparatus for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface ge...
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WO/2008/105789A2 |
To fabricate a joint in a panel (10), a groove (18) is generated and the panel is bent along the groove. The panel includes a first skin (12), second skin (14), and core (16). The core is sandwiched between the first skin and the second ...
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WO/2008/101735A1 |
The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articul...
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WO/2008/100286A2 |
An aircraft can include a wing (42) with a leading edge (64) and a trailing edge (66). The wing has a main body (74) and movable control surfaces (80, 82) coupled to the main body. The wing (42) generates lifting forces when the aircraft...
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WO/2008/097325A2 |
An airfoil for use with an aircraft having an engine (3) positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element (14, 16). The upper surfac...
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WO2008071399B1 |
Wing of an aircraft having a mainplane (20), which has an upper face (22), a lower face (23) and an aerodynamical Iy shaped area (21), and having an additional airfoil (10) which is articulated on the mainplane (20) and can be extended f...
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WO/2008/084260A2 |
A leading edge structure is disclosed for an aircraft wing in which a droop nose is articulated by a double hinge, in particular said leading edge structure comprising: a fixed leading edge structure (201); a movable leading edge structu...
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WO/2008/082437A2 |
An aircraft wing slat (20) is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core (26) sandwiched between upper,(22) and lower (24) composite skins, a pre-cured (...
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WO2008058695B1 |
A high- lift system on the wing of an aircraft and a method for its operation are described. High- lift flaps (2) which are arranged on the wing (1) are extended from a retracted position in order to increase the lift, and a slot (3) thr...
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WO/2008/060325A2 |
A mission control grip mounted to a consol to provide a crew interface with a multitude of systems through a multitude of Multi-Functional Displays (MFDs). The mission control grip includes a fist-shaped grip movable about a first axis a...
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WO/2008/057065A2 |
A system and method for generating lift provided by a multi-element aircraft wing are provided. The system includes a main wing element (14), a slat (12) interconnected to the main wing element, and a flap (16) interconnected to the main...
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WO/2008/054360A2 |
Aerodynamic seals (140) for use with control surfaces (114a) on aircraft (100) are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member (342) and a second seal member (352). The first...
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WO/2008/051286A2 |
Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly (120) that in turn includes a deployable leading edg...
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WO/2008/043164A2 |
A system that acts on a rudder (L) having its stop parts commanded or moved by an actuator (A) is described. The rudder system comprises a reversible mechanical system with movable stop parts working based on control /command signals, ha...
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WO/2008/029095A1 |
A flow control actuator (10) for a body exposed to fluid flow comprises first and second flow surfaces (14, 16) spaced to define an elongate gap (20) therebetween. An elongate control element is disposed in or adjacent the gap and has an...
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WO/2008/009988A2 |
A method of manufacture of a structural member comprising, providing a number of internal elements (16,18,20), each having an aperture formed therein, sequentially assembling the internal elements onto a longitudinal element (14) such th...
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WO/2007/137935A1 |
The invention concerns an apparatus for and a method of producing aerodynamic resistance on an aircraft, comprising at least one braking flap (10), wherein the at least one braking flap can be extended into the airflow around the aircraf...
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WO/2007/138179A1 |
In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter...
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WO/2007/126422A2 |
A pressure sensor includes a pressure sensitive element for sensing a distributed fluid pressure and producing a signal in response. The pressure sensitive element is configured to be mountable on an airfoil (20) or a hydrofoil, for exam...
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WO/2007/120199A2 |
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 ...
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WO2007071384B1 |
A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) wit...
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WO/2007/099285A1 |
An aircraft wing (1) comprises a leading-edge slat (5), the slat including a main body portion (7) and a slat extension (9) arranged at a spanwise end of the main body portion (7). The cross-sectional area of the slat extension (9) is le...
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WO/2007/096624A2 |
An aircraft control surface failsafe hinge configuration (32) is disclosed. The arrangement comprises a drop link configuration (34) which is adapted to attach a control surface (10) to an aircraft structure (301) where the drop link add...
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WO/2007/096171A1 |
In a flaptrack fairing (3) on the wing (2) of an aircraft (1), which flaptrack fairing (3) partly protrudes beyond the trailing edge (7) of the wing (2) in the direction of the longitudinal axis (x) of the wing (2), the invention provide...
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WO2007068450B1 |
The application describes a rudder of a commercial aircraft. According to the invention, the rudder (100) is divided along its longitudinal direction in at least one region, and the parts (100a, 100b) of the rudder (100) can be spread ag...
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