Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 351 - 400 out of 1,215

Document Document Title
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...  
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...  
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...  
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...  
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...  
WO/2007/072259A3
This invention relates to a method and system (10) for controlling the boundary layer of an airfoil (12) to reduce profile drag during flap deflection. The system (10) comprises first means for blowing air from a lower surface (14) of th...  
WO/2007/096624A3
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...  
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 ...  
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...  
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...  
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...  
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...  
WO/2007/074173A3
The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wing...  
WO/2007/071384A3
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...  
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...  
WO/2007/074173A2
The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wing...  
WO/2007/072259A2
This invention relates to a method and system (10) for controlling the boundary layer of an airfoil (12) to reduce profile drag during flap deflection. The system (10) comprises first means for blowing air from a lower surface (14) of th...  
WO/2007/071384A2
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...  
WO/2007/068450A1
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...  
WO/2007/062005A1
Aircraft trailing edge devices (230) , including devices with non-parallel motion paths (241, 242, 243) , and associated methods are disclosed. A device in accordance with one embodiment includes a wing (220) and an inboard trailing edge...  
WO/2007/054150A1
The invention relates to an advanced trailing edge control surface on the wing of an aircraft. The wing (1) comprises on its trailing edge a flap (4) that runs in the direction of the wingspan and can be pivoted into various positions, a...  
WO/2007/056477A1
A mechanism for extending and supporting a high-lift device (14) relative to an airfoil (10) has a pair of support ribs (26) coupled to the airfoil (10). A carrier track (28) is pivotally coupled to the high-lift device (14) and position...  
WO/2007/042398A1
Disclosed is the use of a lacquer comprising a polyurethane matrix based on aliphatic components as well as fillers which are embedded in the polyurethane matrix and increase resistance to abrasion, as an abrasion-resistant coating of (a...  
WO/2007/040747A1
An energy recovery and storage apparatus especially well adapted for use with flight control surfaces (12) on airborne mobile platforms (15) , such as aircraft. In one form the apparatus includes a ram-like element (16) coupled to a port...  
WO/2006/084157A3
Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems (200) in accordance with some embodiments -include- a wing (210) having a trailing edge (211) , and a flap (220) positioned at least partially aft of ...  
WO2006016070A8
The invention concerns a method for improving maneuverability of an aircraft during approach phases before landing followed by flare-out, the aircraft being equipped with air brakes. The invention is characterized in that it consists in ...  
WO/2006/135421A3
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge devic...  
WO/2007/001735A3
Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage (101) with a first porti...  
WO2006108579B1
The present invention relates to a device for adjusting the lift characteristics of an aircraft with a high lift device (2) that is movably attachable to a wing element (1) and that comprises at least one slot covering device (3; 4), whe...  
WO/2007/001735A2
Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage (101) with a first porti...  
WO/2006/135421A2
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge devic...  
WO/2006/133940A1
A lift-augmenting flap, in particular a leading edge flap, for an aerodynamically effective wing with a defined wing profile, in particular for a carrying wing of an aircraft, wherein the wing (10) comprises a wing box (10a) which on a f...  
WO/2006/127204A1
Aerospace vehicle fairing systems (100a, 100b) and associated methods, including fairings that house flap surface drive mechanisms on aircraft (150), are disclosed herein. One aspect of the invention is directed toward a fairing system (...  
WO/2006/108579A1
The present invention relates to a device for adjusting the lift characteristics of an aircraft with a high lift device (2) that is movably attachable to a wing element (1) and that comprises at least one slot covering device (3; 4), whe...  
WO/2006/108648A1
Nowadays, usually landing flap systems are used that comprise a central drive (101) with a central shaft transmission (102) to the drive stations. According to one embodiment of the present invention a landing flap drive system is stated...  
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/2006/085981A1
An improved structure and method for powering the flight of a model airplane by positioning the motors and propellers on the back side of the top wings of an airplane using a single or double-deck wing design so that the propellers and m...  
WO/2006/084157A2
Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems (200) in accordance with some embodiments -include- a wing (210) having a trailing edge (211) , and a flap (220) positioned at least partially aft of ...  
WO/2006/083547A1
Aerospace vehicle leading edge slat devices and corresponding methods are generally disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes an airfoil (102a, 102b) having a leading edge ...  
WO/2006/064102A1
The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements (6I, 6S) and, during a roll control using the ailerons (5G, 5D), steering the upper element (6S) in the roll di...  
WO/2006/059324A1
A method for landing a fixed wing aircraft is provided in which an inversion maneuver is performed so that the aircraft's back is facing the ground, and the aircraft's underside is facing away from the ground. After initiation or complet...  
WO/2006/056160A1
An arrangement for reducing aerodynamic noise at a supplementary aircraft wing (1; 11) hinged to a main wing (2) and extendable after a gap (9) between the main wing (2) and the supplementary wing (1) has been opened, comprises a separat...  
WO2006004570A3
An aircraft motion control mechanism for regulating aircraft motion from a location remote from an aircraft body portion. The aircraft auxiliary control mechanism has at least one control surface support arm connected to and extending fr...  
WO2006004570B1
An aircraft motion control mechanism for regulating aircraft motion from a location remote from an aircraft body portion. The aircraft auxiliary control mechanism has at least one control surface support arm connected to and extending fr...  
WO/2006/028485A1
A 2-D correction system uses intermittent deployment of aerodynamic surfaces (18) to control a spin or fin stabilized projectile (10) in flight; correcting both crossrange and downrange impact errors. Intermittent surface deployment deve...  
WO/2006/029132A1
Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing (110) having a leading edge, a trailing edge, a first deployable l...  
WO/2006/019332A1
In the first variant, the inventive lifting surface (1) is embodied along the span thereof and is provided with symmetrical and asymmetrical double convex profiles. The greatest thickness of each profile is located after the midpoint of ...  
WO/2006/016070A1
The invention concerns a method for improving maneuverability of an aircraft during approach phases before landing followed by flare-out, the aircraft being equipped with air brakes. The invention is characterized in that it consists in ...  
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/2006/010699A1
The invention relates to a mobile leading-edge flap (16) of an aircraft aerofoil element. The inventive flap comprises an aerodynamic skin (18) with a front region (24), an upper surface portion (22) and a lower surface portion (20), as ...  

Matches 351 - 400 out of 1,215