| Document |
Document Title |
|
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/2007/062005A1 |
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...
|
|
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/2006/108648A1 |
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...
|
|
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 ...
|
|
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 ...
|
|
WO/2005/108205A1 |
An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when ...
|
|
WO/2005/102826A1 |
The invention relates to variants of active aerodynamic wings (1-10) which are mountable on any transport means (land, water, rail and air)and can modify an opening angle, thereby making it possible to increase a drag coefficient and sel...
|
|
WO/2005/092703A1 |
Aircraft leading edge device systems and methods for sizing such systems are disclosed. In one embodiment, a spanwise lift coefficient distribution for an airfoil corresponding to at least one design condition and at least one aircraft a...
|
|
WO/2005/084156A2 |
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/2005/077756A1 |
The invention proposes a landing flap guide for aircraft, in which the translatory landing flap (1) movement is realized with a glide slide (4) that is supported and guided in slideways of the landing flap carrier (3). The slide (4) is c...
|
|
WO/2005/070762A1 |
The invention relates to a mobile leading edge flap (16), for a main wing of an aircraft, said flap comprising an aerodynamic skin (18), with a front region subject to bird impacts (24) and a rear skin (28), fixed to the aerodynamic skin...
|
|
WO/2005/062743A2 |
A supersonic aircraft (100) comprises a wing (104) and at least two engine nacelles (122) coupled to the lower surface of the wing on the trailing edge (107). The supersonic aircraft further comprises an inverted V-tail (108) abutting to...
|
|
WO/2005/049424A2 |
An aircraft lift device (100) comprises a strake (102) capable of coupling to an aircraft fuselage (104) and extending to a leading edge (106) of a wing (108). The strake (102) has a leading edge (110). The lift device (100) further comp...
|
|
WO/2005/044661A2 |
A supersonic aircraft (900) comprises a fuselage (901), a wing (904), and a canard (920) coupled onto the fuselage (901) forward of the wing (904) at an elevated position that enables stretching forward of the aircraft lifting length, fo...
|
|
WO/2005/044660A2 |
A supersonic cruise configuration aircraft (100) comprises a fuselage (142) extending on a longitudinal axis from a forward nose (110) to an aft tail (114), and a wing (104) coupled at an inboard section to the fuselage (142) and extendi...
|
|
WO/2005/023643A2 |
An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is als...
|
|
WO2005005251B1 |
Wing of aircraft with slats (1) and one-slotted sliding flaps with driving gear, is characterized by two movable segments in each flap: fore box (2) and main flap (3), which are connected by spring actuators (4) to each other and move on...
|
|
WO/2005/021375A1 |
The invention relates to a support structure for a retractable and extendable flap (12) that is associated with an object (14) surrounded by a flowing liquid. Said support structure has a shell profile (16) that has a fluid/aerodynamic f...
|
|
WO/2005/002962A1 |
A swept aircraft wing includes a leading airfoil element and a trailing airfoil element. At least one full-span slot is defined by the wing during at least one transonic condition of the wing. The full-span slot allows a portion of the a...
|
|
WO/2005/000672A1 |
The invention relates to a wing with variable sustentation for small aeroplanes or ULM planes, said wing being characterised in that it has a flexible wing system (3) that can be continuously deployed in the extension of the rigid wing (...
|
|
WO/2004/108526A1 |
An aircraft (50) comprises first (68) and second (70) wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface (52) attached to an upper surface of the first wing (68), and a second forward openi...
|
|
WO/2004/092520A2 |
An arrangement, and an associated system, in which an actuator is utilized to move a flap. Within the arrangement, an actuator conveys motive force from a motor to cause movement of the flap relative to a supporting structure. A tube of ...
|
|
WO/2004/092013A2 |
A rocket-powered spacecraft with a wing (17) havint hinged portions (21, 22) which can be elevated about a hinge line (23). Tail booms (24, 25) extend rearwardly from the outer ends of the aft wing portions, and rudders (29) are mounted ...
|
|
WO/2004/065209A1 |
A flow-mechanically effective surface of a device moving in a fluid, in particular a flying machine, more particularly a support surface for a flying machine is disclosed, whereby said surface (1) comprises an elastic axis (EA) running i...
|
|
WO/2004/031682A1 |
The aim of the invention is to rapidly bring a ring wheel-shaped textile braking element (16), which is radially deployed by a centrifugal force, into a dimensionally stable contour that is defined at all times even under conditions duri...
|
|
WO/2004/008097A2 |
The invention relates to aircraft flap monitoring. More specifically, the invention relates to a dynamometric rod which is intended to form a pivot for fixing a wing flap, said dynamometric rod comprising a cylindrical body (10) with a h...
|
|
WO/2004/007282A2 |
A preferred embodiment of a rotary-wing aircraft (10) comprises a fuselage (18), a tail boom fixedly coupled the fuselage (18), a pylon fixedly coupled to the tail boom, and a main rotor assembly rotatably coupled to the fuselage and com...
|
|
WO/2004/005132A1 |
A method and apparatus for controlling airflow with a gapped trailing edge having a flexible flow surface. The airfoil (100) comprises a first portion (101) having a first leading edge (111), a first flow surface (114), and a second flow...
|
|
WO/2003/062053A1 |
Joint for connecting a longitudinal side of a first component (4) to the upper side of a second component (T3), comprising at least two co-operating strips (41a, 41b; 42a, 42b; 51a, 51b; 61a, 61b; 71a, 71b), each fixed at the first end (...
|
