Class / Patent application number | Description | Number of patent applications / Date published |
244219000 | Camber | 21 |
20100006708 | WING UNIT, IN PARTICULAR SPAR BOX, FOR FORMING AERODYNAMICALLY ACTIVE SURFACES OF AN AIRCRAFT, IN PARTICULAR AIRFOILS, HORIZONTAL TAIL UNITS OR RUDDER UNITS OF A PLANE - The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane. | 01-14-2010 |
20100025538 | COMPOSITE MATERIAL FOR GEOMETRIC MORPHING WING - An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members. | 02-04-2010 |
20100051752 | Aerodynamic or Hydrodynamic Profile Which Can Be Deformed in a Continuous and Controlled Manner - The present invention relates to an aerodynamic or hydrodynamic profile ( | 03-04-2010 |
20100090067 | AERODYNAMIC PROFILE WITH A REVERSIBLY DEFORMABLE CONTOUR FOR AIRCRAFT, IN PARTICULAR FOR ROTARY WING AIRCRAFT - An aerodynamic profile ( | 04-15-2010 |
20100133387 | SHAPE CHANGING AIRFOIL SYSTEM - A method and apparatus for an airfoil, a flexible skin, and a shape control system. The flexible skin forms a control surface of the airfoil. The shape control system is capable of changing a shape of the control surface formed by the flexible skin between a plurality of shapes, wherein a gap does not occur during a changing of the shape of the control surface. | 06-03-2010 |
20100224734 | MECHANISM FOR CHANGING THE SHAPE OF A CONTROL SURFACE - An apparatus comprises a structure having a first side, a second side substantially opposite to the first side, a flexible skin, and a plurality of deformable assemblies. The flexible skin is attached to the first side and the second side of the structure. The plurality of deformable assemblies is moveably connected to the structure, in which each deformable assembly in the plurality of deformable assemblies has a vertex and a base. The each deformable assembly in the plurality of deformable assemblies has a height that is capable of changing to change a shape of the structure and a shape of the flexible skin. | 09-09-2010 |
20100252687 | ATTACHABLE WING - An attachable wing for an aircraft is disclosed. The attachable wing is configured to mount to the underside of the fuselage of an aircraft, such as a rotary wing aircraft (e.g., a helicopter) or a fixed wing aircraft. The attachable wing produces additional lift, which results in an increase in speed, and consequently, an increase in fuel efficiency and payload capacity. In some embodiments, the attachable wing is retractable to facilitate takeoffs and landings. Additionally, the apparatus may be made of a bulletproof or anti-ballistic material to protect the aircraft from incoming fire or crash damage. The airfoil apparatus provides additional lift, allowing for greater fuel efficiency and range of the aircraft on which it is installed. | 10-07-2010 |
20100258680 | ELONGATED, TORSION-DEFORMABLE AERODYNAMIC ELEMENT - The invention relates to an elongated, torsion-deformable aerodynamic element, in which the upper surface ( | 10-14-2010 |
20100294893 | AERODYNAMIC COMPONENT WITH A DEFORMABLE OUTER SHELL - The invention relates to an aerodynamic component, in particular a wing, a landing flap, a pitch elevator, a yaw rudder, a fin or tail. The aerodynamic component comprises an outer shell and at least one supporting element supporting said outer shell. A drive unit rotates the supporting element. A supporting region is created between the supporting element and the outer shell. The supporting region transfers deformation forces from the drive unit via the supporting element to the outer shell. The supporting element is designed and configured for changing the distance of the supporting region from a longitudinal plane of the aerodynamic component with a rotation of the supporting element. The outer shell comprises an elastic deformation region. The elastic deformation region is elastically deformed by the deformation forces with a rotation of the supporting element. | 11-25-2010 |
20110017876 | Shape-Changing Control Surface - A method and apparatus for controlling the shape of a control surface. A structure is rotated about an axis. The structure is located between a flexible skin and a skin located substantially opposite of the flexible skin. An assembly is moved to change the shape of the control surface in response to a rotation of the structure. The assembly is movably connected to the structure and is configured to move such that the flexible skin forms a plurality of curvatures. | 01-27-2011 |
20110163205 | AEROFOIL ACCESSORIES AND METHOD FOR MODIFYING THE GEOMETRY OF A WING ELEMENT - Aerofoil accessories are provided, configured for selective attachment to a wing element, the wing element having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories are each configured for having a substantially fixed geometric profile with respect to the at least one datum aerofoil section at least whenever said wing element is airborne with the respective accessory attached to the wing element. The modified geometric profile is such as to provide said wing element with the accessory attached thereto with a desired change in performance relative to a datum performance provided by the wing element absent the accessory. A kit is also provided for enhancing performance of a wing element in off-design conditions. A method is also provided for enhancing performance of a wing element in adverse conditions. | 07-07-2011 |
20120104181 | Cross-Sectionally Morphing Airfoil - The present invention provides an apparatus, system, and method for morphing the cross-sectional shape of an airfoil between a high-speed, low-lift airfoil and a low-speed, high-lift airfoil, including interim airfoil configurations, to allow for optimal performance. This is done by inputting a control command into the system that alters the shape of the split or elastic upper and/or lower skin surface to allow the airfoil camber and chord to vary. | 05-03-2012 |
20120104182 | PNEUMATIC CONTROL SYSTEM FOR AERODYNAMIC SURFACES - A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface. | 05-03-2012 |
20130043354 | VARIABLE CAMBER FLUID-DYNAMIC BODY UTILIZING OPTIMIZED SMART MATERIALS - A system and methods for configuring a fluid-dynamic body is disclosed. A camber of a fluid-dynamic body is configured by activating a shape memory alloy actuator coupled to the fluid-dynamic body. | 02-21-2013 |
20130099063 | Segmented Aircraft Wing Having Solar Arrays - An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature. | 04-25-2013 |
20130146717 | WING VARIABLE CAMBER TRAILING EDGE TIP - A flexible tip for integration in a wing trailing edge employs a wing structure rear spar. A flexible upper skin is attached at a forward boundary to the spar and a rigid lower skin is interconnected to the flexible upper skin at a rigid tail piece. At least one actuation link is attached to the rigid tail piece and has a hinge at a forward edge of the rigid lower skin. At least one positioning slider is attached to the hinge which is movable from a neutral position to a first extended position urging the hinge aft for rotation of the rigid lower skin upward and flexing of the flexible upper skin in an upward camber and to a second retracted position urging the hinge forward for rotation of the rigid lower skin downward and flexing of the flexible upper skin in a downward camber. | 06-13-2013 |
20150321750 | DRIVE SYSTEM FOR A VARIABLE CAMBER AIRCRAFT WING - The present invention relates to a drive system for a variable camber aircraft wing having position variable front flaps and/or rear flaps, having drive shafts, which are arranged such that that the flaps undergo a change of position in operation of the drive shafts, and having one or more drive units in driving connection with the drive shafts, wherein at least one switchable coupling is provided via which the drive shafts of two flaps of an aircraft wing can be coupled to one another. | 11-12-2015 |
20160090169 | DEVICE FOR SIMULTANEOUSLY AND PROGRESSIVELY VARYING THE CAMBER AND THE ANGLE OF ATTACK OF HYDRODYNAMIC AND AERODYNAMIC WINGS - A device for simultaneously and progressively varying the camber and the angle of attack of a hydrodynamic and aerodynamic profile of a wing, the latter being able to adopt multiple positions including a position at rest, the said profile at rest being in a plane, the device having a wing with a profile having a leading edge at the front and a trailing edge at the rear, a seat arranged in the upper part of the profile of the wing connected at one of its ends to the front upper part of the profile by a first pivot, and at its other end to a lever by a connection point, a lever connected to the rear upper part of the profile by a second pivot, and that at rest, a seat and at least one lever are aligned or substantially aligned along the same axis and are included in the same plane as the profile. | 03-31-2016 |
20160159455 | CHANGEABLE WING PROFILE - This relates to changes in wing profiles. In order to provide an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises an adaptive surface support structure in a longitudinal direction, which extends in a longitudinal direction from a root area to an outer end area, and is formed by a support surface, which comprises an adjustable periodic profiling that runs in the transverse direction, in which first flange areas and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height. Alternatingly aligned open profile segments running in the longitudinal direction are here formed. | 06-09-2016 |
20160159456 | CHANGEABLE WING PROFILE - This relates to changes in wing profiles. In order to make available an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area. The support structure also comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements The framework segments are joined to the fixed spar. At least one side of a portion of the triangular compartments comprises one of the adjustable guide elements, so that the shape of the framework segments can be adjusted. | 06-09-2016 |
20160185443 | DUAL-RIB MORPHING LEADING EDGE - A mechanism for changing a shape of a leading edge of an airfoil may include a first rib and a second rib. The first rib may include a plurality of first rib segments. The first rib may move between a first folded shape and a first extended shape. The second rib may include a plurality of second rib segments. The second rib may move between a second folded shape and a second extended shape. An actuator may be coupled to the first rib, the second rib, or both, to move the first rib, the second rib, or both, between their respective folded and extended shapes. | 06-30-2016 |