| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244199100 | By vortex control outside of boundary layer | 77 |
| 20080203233 | Flueted aircraft wing - The flueted aircraft wing has one or more thin Streamline Flow Panels placed longitudinally over the upper surface of an aircraft wing, and extend out in front of the wing leading edge. These panels capture airflow from along the wing leading edge in addition to the relative wind flow ahead of the wing, and direct the total airflow over the surface of the wing. The Streamline Flow Panels partition regions of vortex airflow over the wing and reduce transverse airflow. Wing tip vortices and induced drag are greatly reduced, and lift is increased. Fuel economy is substantially improved because airflow energy losses are reduced. | 08-28-2008 |
| 20090039203 | Device for Controlling a Vortex Trail Generated by the Oblong Element of an Aircraft Bearing Surface - A device for controlling a vortex trail generated by the oblong element of an aircraft bearing surface comprises a control means ( | 02-12-2009 |
| 20090289149 | Engine pod for an aircraft with a vortex generator arrangement - The invention pertains to an engine pod for an aircraft, one side of which features several fin-shaped vortex generators ( | 11-26-2009 |
| 20100038492 | RETRACTABLE NACELLE CHINE - A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall. | 02-18-2010 |
| 20100176249 | Engine Nacelle Of An Aircraft Comprising A Vortex Generator Arrangement - An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔. | 07-15-2010 |
| 20100294890 | METHOD AND DEVICE FOR REDUCING THE INDUCED SPEEDS IN VORTICES IN THE WAKE OF AN AIRCRAFT - A method and a device for creating a continuous protected space along the path of an aircraft, in which protected space a maximum induced speed Vtc in a vortex of radius Rtc in the wake of an aircraft is decreased by increasing the radius Rtc. The method includes a preliminary step of identifying changes in the aerodynamic configurations of the aircraft liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, —for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex, —carrying out, along the course of the aircraft, at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space. | 11-25-2010 |
| 20110101168 | Method of Controlling an Aircraft in Flight, Especially to Reduce Wake Vortices - The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter. | 05-05-2011 |
| 20110272529 | Hamilton H.N2 laminar flow diskette wing - A wing assembly has a wing and one or more no-bias laminar flow oval diskettes that are fixed on a support structure along the C/L (center of lift) of an airfoil, of an aircraft wing. The benefit of an oval diskette with laminar flow is that it has no speed limitations and it allows an aircraft to clime at a speed that matches its Ground Effect Lift speed which is a 25% performance increase and a 40% reduction in vortex drag with a increase stability that eliminates inertia coupling of high-speed airfoils. | 11-10-2011 |
| 20140070056 | ARICRAFT WITH IMPROVED AERODYNAMIC PERFORMANCE - An aircraft ( | 03-13-2014 |
| 20140217240 | VORTEX GENERATING APPARATUS AND VORTEX GENERATING METHOD - A vortex generating apparatus includes: a member to contact with a flow of a fluid to form a stagnation point and a first and a second separation points on a periphery of a cross section of the member parallel to the flow; a disturbance applying unit to apply a disturbance to an upstream side of the first separation point to cause part of a boundary layer of the flow to adhere; and a controller to temporally control the application of the disturbance to change an adhesion distance from the stagnation point to the first separation point so as to generate a dynamic stall vortex. | 08-07-2014 |
| 20160031550 | SUBMERGED VORTEX GENERATOR - A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow. | 02-04-2016 |
| 244199200 | Of tip vortex | 66 |
| 20080217484 | BRAKE FLAP FOR AN AIRCRAFT - A brake flap is provided for an aircraft, which brake flap, for the purpose of delaying the aircraft, can be set at an angle relative to the airstream flowing around it. The flap comprises a free edge which when set at an angle is spaced apart from the exterior skin of the aircraft, and generates an edge vortex in the airstream flowing around said aircraft. The free edge comprises a number of individual edge sections that divide the edge vortex into a number of partial vortices. | 09-11-2008 |
| 20100187366 | Reduction of Tip Vortex and Wake Interaction Effects in Energy and Propulsion Systems - An airfoil includes a plasma actuation surface integrated onto the airfoil surface. On the airfoil, the plasma actuation surface is configured to provide high-frequency plasma actuation along the plasma actuation surface such that excitation of the vortex flow or shear flow mitigates the vortex flow or the shear flow associated with the airfoil. | 07-29-2010 |
| 20130153711 | Minimally intrusive wingtip vortex wake mitigation using inside-mold-line surface modifications - An airfoil tip vortex mitigation device comprising an intake port disposed in a first surface of an airfoil and an exit port in fluid communication with the intake port and disposed in a second surface of the airfoil where air pressure is less than at the first surface when the airfoil is producing lift. The channel and exit port are positioned and configured to direct diverted air in such a way as to weaken an airfoil tip vortex that's produced by the airfoil when the airfoil is producing lift. | 06-20-2013 |
| 20130299643 | Vortex Generation - A vortex generation apparatus including a vortex generator that deploys in response to deployment of a wing leading edge lift augmentation device. The vortex generator deploys into a position to generate vortices over a main wing body upper surface region trailing the vortex generator. | 11-14-2013 |
| 244199300 | Active | 5 |
| 20090173835 | SYSTEMS AND METHODS FOR DESTABILIZING AN AIRFOIL VORTEX - Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated. | 07-09-2009 |
| 20100006706 | AERODYNAMIC BODY AND CARRIER WING COMPRISING AN AERODYNAMIC BODY, ACTUATING DRIVE CONTROL MODULE, COMPUTER, COMPUTER PROGRAM AND METHOD FOR INFLUENCING POST-TURBULENCES - An aerodynamic element attachable to a primary wing to extend in a longitudinal direction at an angle to a spanwise direction of the primary wing. The aerodynamic element includes a downstream end having at least two flow flaps arranged next to each other and oriented in the longitudinal direction of the aerodynamic element. | 01-14-2010 |
| 20110101169 | DEVICE FOR THE GENERATION OF AERODYNAMIC VORTICES AND ALSO A REGULATING FLAP AND WING WITH A DEVICE FOR THE GENERATION OF AERODYNAMIC VORTICES - A device for the generation of aerodynamic vortices to be arranged on the spanwise side edge of a wing, or a regulating flap adjustably arranged on the latter, which in each case have a chordwise direction and a spanwise direction, wherein the device is formed from one aerofoil component or from a plurality of aerofoil components, wherein the at least one aerofoil component is designed as a part that can be moved relative to the wing or regulating flap in its spanwise direction, wherein the device for vortex generation has an actuation device for the retraction and extension of the aerofoil components into a recess, and also a drive device to operate the actuation device. A regulating flap of a wing, and also a wing, with such a device for the generation of aerodynamic vortices, and a wing, which has at least two aerofoil segments at its side edge situated at the spanwise end. | 05-05-2011 |
| 20130001367 | METHOD FOR REDUCING IN FLIGT WAKE VORTICES AND AN AIRCRAFT WINGTIP ARRANGEMENT USED IN SUCH METHOD - This invention discloses a wingtip ( | 01-03-2013 |
| 20150360770 | LOCK ACTUATION SYSTEM FOR AIRCRAFT - Described herein is a system that includes an actuator with a movable input, a first summing mechanism with an input, a first output, and a second output. The input of the first summing mechanism is movably driven by the movable input of the actuator and the first output of the first summing mechanism is movably coupled to a first actuatable element. The system also includes an end mechanism with an input and a first output. The input of the end mechanism is movably driven by the second output and the first output of the end mechanism is movably coupled to a second actuatable element. The system further includes a sensor that senses a position of the rotational input of the actuator. A status of the first and second actuatable elements is based on a sensed position of the movable input of the actuator. | 12-17-2015 |
| 244199400 | Wing tip foils/fences | 57 |
| 20080223991 | Wing Tip Device - An aircraft comprises a wing having a positive dihedral, the wing comprising a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight. | 09-18-2008 |
| 20080308683 | CONTROLLABLE WINGLETS - Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing. | 12-18-2008 |
| 20090014592 | CO-FLOW JET AIRCRAFT - The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust. | 01-15-2009 |
| 20090039204 | Wingtip Feathers, Including Forward Swept Feathers, and Associated Aircraft Systems and Methods - Tip feathers, including forward swept tip feathers, and associated aircraft systems and methods are disclosed. A system in accordance with one embodiment includes an aircraft wing having an inboard portion, an outboard portion, and a leading edge having an aft wing sweep angle at the outboard portion. A first feather is fixed relative to, and projects outwardly from, the outboard portion of the wing and has a leading edge with a first, forward sweep angle relative to a pitch axis of the wing. A second feather is fixed relative to, and projects outwardly from, the outboard portion of the wing at least partially aft of the first feather, and has a leading edge with a second, aft sweep angle relative to the pitch axis. | 02-12-2009 |
| 20090084904 | Wingtip Feathers, Including Paired, Fixed Feathers, and Associated Systems and Methods - Wingtip feathers, including paired, fixed features, and associated systems and methods are disclosed. A method for designing an aircraft wing in accordance with a particular embodiment includes providing a geometry for a wing having an upper surface, a lower surface, and an aft-swept wing leading edge. The method can further include selecting a geometry and location for a first feather and a second feather, based at least in part on a predicted effect of the feathers on a location of a shock at the upper surface of the wing at transonic flight conditions, with the first feather being positioned at an outboard tip of the wing and the second feather being positioned at the outboard tip of the wing aft of the first feather. | 04-02-2009 |
| 20090206206 | Highly efficient supersonic laminar flow wing - Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following:
| 08-20-2009 |
| 20090256029 | Winglets with Recessed Surfaces, and Associated Systems and Methods - Winglets with recessed surfaces, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing having an inboard portion and an outboard portion, and further includes a winglet coupled to the wing at the outboard portion. The winglet can have a first surface facing at least partially inboard and a second surface facing at least partially outboard, with the first surface including a recessed region. | 10-15-2009 |
| 20090302167 | Apparatus and method for use on aircraft with spanwise flow inhibitors - An aircraft can include a wing with a leading edge and a trailing edge. The wing has a main body and movable control surfaces coupled to the main body. The wing generates lifting forces when the aircraft is in flight. The movable control surfaces can be used to control the generated lifting forces. A spanwise flow inhibitor extends from the outer wingtip of the wing. At least one gurney flap extends generally downwardly from at least a portion of the trailing edge of the wing. The flap at least partially counteracts a change in center of lift attributable to the spanwise flow inhibitor. | 12-10-2009 |
| 20100019094 | WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT - A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction. | 01-28-2010 |
| 20100148010 | AIRCRAFT WING MODIFICATION AND RELATED METHODS - A transferable modified leading edge for a wing is detachably mountable to a parent wing. The parent wing may use a NACA 23000-series airfoil. A modified wing tip may be used in conjunction with the modified leading edge. The modified leading edge can be mounted to a parent wing in a way that does not damage the parent wing. The modified leading edge and wing tip can provide increased lift. | 06-17-2010 |
| 20100155541 | WINGLET - A winglet comprising a root connected to a distal end of a wing; an upwardly angled section; a tip; and a transition between the upwardly angled section and the tip at which an outboard cant angle of the winglet decreases relative to a reference plane of the wing. In one embodiment the winglet is continuously curved and includes a point of inflection at which the span-wise curvature of the winglet changes sign. In another embodiment the upwardly angled section is planar. The winglet generates a tip vortex when in flight. The tip vortex is displaced outboard from the winglet due to the decrease in outboard cant angle at the transition. | 06-24-2010 |
| 20100181432 | Curved Wing Tip - A wing incorporating a wing tip with a curved leading edge and a curved trailing edge to minimize induced drag for a given wing form is disclosed. The curve of the leading and trailing edges of the wing tip may be described generally as parabolic, elliptic, or super elliptic. A finite tip segment may be included with a sweep angle between the end of the curved leading edge and the end of the curved trailing edge. The wing tip may also include a spanwise camber. | 07-22-2010 |
| 20100294891 | WINGTIP EXTENSION FOR REDUCTION OF VORTEX DRAG IN AIRCRAFT - The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing. | 11-25-2010 |
| 20110024573 | EXTENDED WINGLET WITH LOAD BALANCING CHARACTERISTICS - A winglet and methods of operating an aircraft using the winglet. In some embodiments, the winglet can be mounted to the wingtip of an aircraft and has three segments or portions, namely, a mounting portion, an upwardly extending portion, and a reverse portion, or a portion that extends in an inboard direction. | 02-03-2011 |
| 20110127383 | ACTIVE WINGLET - An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency. | 06-02-2011 |
| 20110186689 | ACTIVE WINGLET - An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency. | 08-04-2011 |
| 20110192937 | NON-PLANAR WING TIP DEVICE FOR WINGS OF AIRCRAFT, AND WING COMPRISING SUCH A WING TIP DEVICE - A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device. | 08-11-2011 |
| 20110226908 | Encased Square Wing - The invention relates to an aerodynamic wing in the shape of a tubed perfect square, the vertical stabilizers and air brake being built into the structure thereof, characterized in that said wing reduces induced drag and increases the efficiency of aircraft in flight. | 09-22-2011 |
| 20110260008 | Fluid flow control device for an aerofoil - A fluid flow control device for an aerofoil comprises an aerofoil-tip body of aerofoil shape, coupling apparatus adapted to couple one end of the body to an aerofoil, and a passive tip blowing assembly. The passive tip blowing assembly is provided at the other end of the aerofoil-tip and comprises a housing defining a fluid chamber and a vane of aerofoil shape. The fluid chamber extends along part of the chord-length of the body and has a fluid inlet and a fluid outlet. The vane is arranged along the chord of the aerofoil-tip, with its leading edge at the inlet and its trailing edge at the outlet. The aerofoil section of the aerofoil-tip has a higher camber than that of the aerofoil, which turns fluid flow across the low pressure side of the aerofoil towards the aerofoil-tip, so that the fluid flow mirrors the fluid flow across the high pressure side of the aerofoil. | 10-27-2011 |
| 20110272530 | WING TIP DEVICE - An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight. | 11-10-2011 |
| 20120187251 | Multiple Controllable Airflow Modification Devices - An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, and/or increase efficiency. | 07-26-2012 |
| 20120248255 | WING TOP POD - A natural-laminar-flow swept transonic wing fitted with a wing tip pod for controlling the location of a wing shock in the wing tip region, such that the shock extends outboard substantially up to the wing tip without substantially sweeping forward toward the wing tip leading edge. | 10-04-2012 |
| 20120312928 | Split Blended Winglet - A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally upward projecting wing end to form a winglet assembly or may be separately attached onto an existing upwardly curved winglet. | 12-13-2012 |
| 20120312929 | Split Spiroid - The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane. | 12-13-2012 |
| 20130099060 | Hinged Raked Wing Tip - A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces. | 04-25-2013 |
| 20130146715 | Minimally intrusive wingtip vortex wake mitigation using microvane arrays - An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil. | 06-13-2013 |
| 20130193273 | WINGTIP FIN OF AN AIRCRAFT - A wingtip fin of an aircraft comprising an upstanding fin body, the fin body having an inboard face and an outboard face and a recess defined there within, a display screen assembly in the recess in the fin body, the display screen assembly comprising a translucent face, substantially flush with and forming at least part of the inboard face or the outboard face of the fin body, and a display screen arranged in the recess such that images displayed on the display screen are visible through the translucent face. | 08-01-2013 |
| 20130256460 | PERFORMANCE-ENHANCING WINGLET SYSTEM AND METHOD - A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing. | 10-03-2013 |
| 20130320150 | WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT - A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased. | 12-05-2013 |
| 20130341466 | WING COMPRISING A FLOW FENCE, AND AIRCRAFT HAVING SUCH WINGS - A wing of an aircraft has a pressure-side flow surface and a suction-side flow surface relative to an assumed main direction of attack and comprises a flow fence disposed on a flow surface, wherein the flow fence extends in the main wing chordwise direction and between a location of the pressure-side flow surface and a location of the suction side flow surface. | 12-26-2013 |
| 20140014780 | HIGH-LIFT DEVICE OF FLIGHT VEHICLE - A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion. | 01-16-2014 |
| 20140117166 | NATURAL LAMINAR FLOW WINGTIP - An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith. | 05-01-2014 |
| 20140291453 | WING LOAD ALLEVIATION METHODS AND APPARATUS - Wing load alleviation methods and apparatus are disclosed. An example winglet system for an aircraft includes a first winglet including a body portion having a leading edge and a trailing edge, a base portion to be coupled to an outboard end of a wing such that the body portion projects at an upward angle from the wing during all modes of airplane operation, a control surface coupled to the body portion proximate to the trailing edge, and at least one of a spoiler and an aileron coupled to the outboard end of the wing; and a processor to, in response to at least one input signal indicative of one of a subset of flight conditions, command actuated deflections of both the control surface of the first winglet and the at least one of the spoiler and the aileron to create an incremental pressure field in an airflow region inboard of the first winglet. | 10-02-2014 |
| 20140306067 | CONTROLLABLE AIRFLOW MODIFICATION DEVICE PERIODIC LOAD CONTROL - An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency. | 10-16-2014 |
| 20140312174 | WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT - A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction. | 10-23-2014 |
| 20140346281 | Split Blended Winglet - A split winglet configured for attachment to a wing of an airplane. The split winglet may include an upper winglet smoothly extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet may include a transition section which curves upward from the wing tip into a substantially planar section. Upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges which are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Similarly, upper and lower surfaces of the ventral fin may be bounded by leading and trailing edges which curve toward the airstream direction and terminate at a point distal of the wing tip. | 11-27-2014 |
| 20150008291 | Active Winglet - An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency. | 01-08-2015 |
| 20150028160 | WINGTIP FOR A GENERAL AVIATION AIRCRAFT - A wingtip for extending a wing of an aircraft having a NACA 23012 airfoil. The wingtip has an airfoil design for directing and associated wingtip vortex outward and upward to thereby increase the effective wingspan of the aircraft and to reduce induced drag. The wingtip is preferably molded and comprises a fuel tank bay, internal antenna, landing light and navigation light. | 01-29-2015 |
| 20150041597 | WINGTIP DEVICE OF A WING, AND ALSO A WING WITH SUCH A WINGTIP DEVICE - A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided. | 02-12-2015 |
| 20150321746 | FIXED WING OF AN AIRCRAFT - A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K | 11-12-2015 |
| 20160001876 | WING TIP DEVICE - A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting With the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection. | 01-07-2016 |
| 20160009378 | ADJUSTABLE LIFT MODIFICATION WINGTIP | 01-14-2016 |
| 20160009380 | WINGLET SYSTEM AND METHOD | 01-14-2016 |
| 20160031551 | LAMINAR FLOW WINGLET - An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith. | 02-04-2016 |
| 20160068258 | Aircraft with C-Shaped Carrier Surfaces and Movable Top Surfaces - An aircraft with C-shaped carrier surfaces wherein an axis of rotation of top surfaces is arranged in the respective aerodynamic center of the top surfaces, furthermore that each top surface can be adjusted by an adjustment device that can be controlled by a control device, wherein an angle of attack of the top surfaces can be adjusted that is optimal for a minimal induced resistance based on flight state parameters. This arrangement minimizes the adjusting moment during the adjusting of the top surfaces and is independent of the angle of attack of the top surface. | 03-10-2016 |
| 20160068259 | WINGLET SYSTEM - A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. | 03-10-2016 |
| 20160075425 | BRAIDED COMPOSITE SPAR - A braided composite spar or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar or preform has a centre line which extends lengthwise from a root to a tip, and at least part of the centre line follows a curved path which does not lie in a single plane. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. | 03-17-2016 |
| 20160075426 | BRAIDED COMPOSITE SPAR - A braided composite spar or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar or preform extends lengthwise from a root to a tip, and the spar or preform has a tapered portion in which each ply has a height which reduces and a width which increases as it extends toward the tip. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. | 03-17-2016 |
| 20160075427 | BRAIDED COMPOSITE SPAR - A braided composite spar or preform for a braided composite spar with a plurality of tubular plies of braided fibres. Each ply has a first set of fibres which wind in a clockwise direction in a first series of turns with a pitch between each adjacent pair of turns, and a second set of fibres which wind in an anti-clockwise direction in a second series of turns with a pitch between each adjacent pair of turns. The first and second sets of fibres in each ply are intertwined to form a braided structure. The spar or preform extends lengthwise from a root to a tip and has a tapered portion which tapers inwardly towards the tip. Each ply has a circumference in the tapered portion which reduces as it tapers inwardly. For at least one of the plies the pitches of the first and second sets of fibres increase continuously as the ply tapers inwardly in the tapered portion. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. | 03-17-2016 |
| 20160075429 | WINGLET - A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web, an upper front spar cap, and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap. The winglet is manufactured by co-curing the upper skin to the upper main spar cap and the upper front spar cap; and co-curing the lower skin to the lower main spar cap and the lower front spar cap. | 03-17-2016 |
| 20160144951 | WING TIP DEVICE FOR AN AIRCRAFT WING - A wing tip device for an aircraft wing may include an upper winglet and a lower element. The upper winglet may extend upwardly from an aircraft wing. The lower element may extend downwardly from the upper winglet and may form a closed loop below the wing. The closed loop may have a hollow interior. | 05-26-2016 |
| 20160159467 | Split Spiroid - The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane. | 06-09-2016 |
| 20160167769 | HIGH-LIFT DEVICE OF FLIGHT VEHICLE | 06-16-2016 |
| 20160185450 | AIRCRAFT WINGLET DESIGN HAVING A COMPOUND CURVE PROFILE - An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets ( | 06-30-2016 |
| 20160194073 | HIGH-LIFT DEVICE OF FLIGHT VEHICLE | 07-07-2016 |
| 20170233065 | CURVED WINGTIP FOR AIRCRAFT | 08-17-2017 |
| 20220135212 | AIRCRAFT ASSEMBLY INCLUDING A WINGTIP DEVICE - An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation. | 05-05-2022 |
