| Entries |
| Document | Title | Date |
|---|
| 20080283672 | 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. | 11-20-2008 |
| 20080302918 | CONTROL SURFACE ASSEMBLIES WITH TORQUE TUBE BASE - Control surface assemblies having a torque tube base are disclosed. In one embodiment, a method includes providing a control surface assembly including: providing a control surface portion having a pair of longitudinal surfaces, providing a hollow base portion coupled to the control surface portion, the base portion including an elongated curved wall, and an elongated base plate disposed crosswise to the pair of the longitudinal surfaces having at least one aperture disposed therein, and a plurality of attachment flanges extending laterally outwardly beyond the longitudinal surfaces; coupling the attachment flanges to a supporting structure of a vehicle such that the control surface portion projects outwardly from the supporting structure; moving the vehicle through a medium; and moving at least a portion of the control surface assembly to generate a force on the vehicle. | 12-11-2008 |
| 20090001223 | Flexible Control Surface for an Aircraft - A flexible control surface ( | 01-01-2009 |
| 20090014594 | JACK SYSTEM WITH AUTOMATIC LOCKING OF THE PISTON IN HIGH POSITION, ESPECIALLY FOR AIRCRAFT - This invention provides a jack system ( | 01-15-2009 |
| 20090127402 | SLAT SUPPORT FUNK PLATE - An aircraft wing high lift assembly comprising a movable element and a load receiving element including a body portion having a first load receiving region arranged to receive loads from the movable element in a first direction during normal operation of the high lift assembly and including at least one restraining arm projecting from the body portion, the or each restraining arm having a second load receiving region arranged to receive loads from the movable element in a second direction in the event of a failure within the high lift assembly. | 05-21-2009 |
| 20090127403 | LIFT FLAP CARRIER SYSTEM - Device for carrying lift flaps arranged on the wings of an aircraft and a wing. The device includes a carrier with a U-shaped profile, a covering plate positionable over an open side of the U-shaped profile, and a fairing housing formed in an aerodynamic manner and at least in part by the carrier. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way. | 05-21-2009 |
| 20090146013 | FLIGHT CONTROL USING ACTUATED VARIABLE MOMENT ARM - Systems and techniques are described for actuating a control surface about a pivot point using variable moments. A bracket having a moment arm is coupled to the pivot point such that the bracket is rotatable about the pivot point to actuate the surface. A power actuator has a shaft coupled to the bracket at a coupling point on the moment arm such that actuation force applied to the shaft results in a moment produced about the pivot point. A linear actuator is configured to adjust the location of the coupling point with respect to the pivot point to thereby changing the moment arm and the moment produced about the pivot point as the bracket rotates. By adjusting the distance between the pivot point and the coupling point, the moments produced about the pivot point can be increased while conserving actuator power. | 06-11-2009 |
| 20090146014 | Actuation System for a Lift Assisting Device and Roller Bearings Used Therein - An actuation system for deploying and retracting a lift assisting device of a wing of an aircraft, is presented. The actuation system includes a track pivotally coupled to the lift assisting device, a shaft rotating in response to flight control signals to deploy or retract the lift assisting device, means for actuating the lift assisting device between a retracted position and a deployed position along an arcuate path, a plurality of track roller bearings and a plurality of side roller bearings. The roller bearings rotatably contact the track to guide the track along the arcuate path. The track roller bearings are comprised of an outer ring, a split inner ring and liners disposed between bearing surfaces of the outer and the inner rings. The split inner ring is configured for accommodating deflection and bending of a mounting pin coupling the track roller bearing in proximity to the track. | 06-11-2009 |
| 20090146015 | Aircraft highlift system - The present invention relates to an aircraft high-lift system with at least one drive unit for operating the high-lift systems of the half wings (half-wing systems) and with at least one overload protection to avoid undesirably high operating torques in the half-wing systems, wherein the overload protection includes a comparator, by means of which the instantaneous values of the operating torques of the half-wing systems are compared and/or a condition caused by the difference of the operating torques is detected, and a limiter connected with the comparator, by means of which the drive unit is blocked, shut down or deactivated, and/or the torque of the drive unit is dissipated into the aircraft structure, when the difference of the operating torques determined in the comparator exceeds a limit value. | 06-11-2009 |
| 20090200431 | AIRCRAFT WING TIP HAVING A VARIABLE INCIDENCE ANGLE - An embodiment of an aircraft wing includes a main wing section and a variable incidence wing tip. The main wing section is adapted to connect to an aircraft fuselage at a first angle of incidence. The variable incidence wing tip is connected to the main wing section so that the variable incidence wing tip is rotatable to angles of incidence that are different from the first angle of incidence. An embodiment of a method for operating an aircraft includes generating a control signal based on an indication of a desired angle of incidence of a variable incidence wing tip, conveying the control signal to a wing tip rotation mechanism, and rotating the variable incidence wing tip in accordance with the control signal, so that the angle of incidence of the variable incidence wing tip is different from an angle of incidence of the main wing section. | 08-13-2009 |
| 20090308981 | AIRCRAFT WING ASSEMBLY - An aircraft wing assembly comprising: a main wing element; an inboard rib and an outboard rib, each mounted to the main wing element; a bridging structure attaching the inboard rib to the outboard rib; an inboard flap and an outboard flap; and an inboard bearing and an outboard bearing, each mounted to the bridging structure and each engaging a respective one of the flaps. The bridging structure ensures that an accurate distance is maintained between the ribs during installation, and maximises the stiffness of the assembly. Also, the bridging structure can act as a shear plate supporting both the inboard and outboard bearings, thus removing any twisting moment on the ribs. | 12-17-2009 |
| 20090321581 | FLAP DEVICE - A flap device adapted for location on or in a fluid interfacing surface such as an airfoil section, the device comprising a housing, a flap mounted for rotation at least partially within the housing, an entry in a leading portion of the housing, and at least one stop member associated with the housing and actuable between a non-operative parked position and an operative position in which in use the stop member is adapted to limit the movement of the flap within the housing thereby to vary the coefficient of lift and drag of the fluid interfacing surface or airfoil section. | 12-31-2009 |
| 20100019096 | ACTUATOR DEVICE BASED ON A SHAPE MEMORY ALLOY, AND A WING FLAP ASSEMBLY FITTED WITH SUCH AN ACTUATOR DEVICE - A wing-flap assembly includes a flap made up of a plurality of flap sections, in which each flap section is connected to the preceding one in a rotatable manner, and one or more actuator devices adapted to control the rotation of the flap sections. Each actuator device includes an extended element made of shape memory alloy and an arch-shaped framework made of elastic material, to which the extended element is fixedly connected under tension. Each end of the extended element is fixed to a respective end of the arch-shaped framework. At least one of the actuator devices is connected at one end to the first of the flap sections, and on the other side it is adapted to be connected to a wing structure. | 01-28-2010 |
| 20100187367 | SPRING TRACK ROLLER ASSEMBLY - A roller assembly comprises a first race and a second race. The second race is coaxial with the first race and is axially movable relative to the first race. The first and second races are movable between a static axial position and a dynamic axial position relative to one another. The roller assembly includes at least one biasing member that is operative to bias the first and second races from the dynamic axial position toward the static axial position. | 07-29-2010 |
| 20100288887 | Hinge sealing element and an assembly including said element - A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin. | 11-18-2010 |
| 20110001015 | Drive Arrangement - A drive arrangement comprising first and second actuators ( | 01-06-2011 |
| 20110042525 | SUPPORT ASSEMBLY - A support assembly ( | 02-24-2011 |
| 20110042526 | METHOD FOR REDUCING THE TAKEOFF RUN OF AN AIRCRAFT - The method of the invention comprises imparting to the flaps ( | 02-24-2011 |
| 20110101174 | High Lift System For An Aircraft - A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by means of flap actuating means and a drive device, said system further comprising a carrier part disposed on the main wing to which the flap actuating means are coupled and relative to which the flap actuating means for adjusting the flap can be moved, wherein the carrier part is disposed on the main wing by means of a bearing device comprising an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted. | 05-05-2011 |
| 20110101175 | High-Lift Device Track - The present invention relates to a high-lift device track | 05-05-2011 |
| 20110114795 | Aerodynamic Flap and Wing - An aerodynamic flap with an articulation device to form an axis of rotation for purposes of a rotatable mounting of the aerodynamic flap on a wing section or structural section, with the flap coupled to the wing section in accordance with its intended purpose, with a front flap section situated upstream of the axis of rotation, as viewed in the flow direction, with a front edge line, and a rear flap section situated behind the axis of rotation, wherein a multiplicity of extension pieces are arranged on the front flap section, distributed over the span width of the flap, whose ends project beyond the front edge line of the flap as exposed parts, as viewed from the axis of rotation, wherein the extension pieces are rigid and arranged on the flap, such that one surface of the extension pieces forms an aerodynamically uniform surface with the upper or lower side of the flap, and such that when the flap is deflected the exposed ends of the extension pieces on one surface of the flap are directed at an angle against the flow to generate vortices, and in a neutral position of the flap are situated underneath the boundary layer of the wing, as well as a wing with such an aerodynamic flap. | 05-19-2011 |
| 20110163204 | HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH A HIGH LIFT FLAP AND METHOD FOR ADJUSTING THE HIGH LIFT FLAP - A high lift system for an aircraft with at least one high lift flap arranged on each of the main wings of the aircraft. The high lift system includes an input device for the generation of flight phase-related requirements for the high lift flap. The high lift system further includes a control device, with a conversion function with which the flight phase-related requirements are converted into setting commands for the actuation of a lift device for the adjustment of the high lift flap. The conversion function is configured such that from a take-off requirement, a setting command to the drive device is generated with which the leading edge flap of the high lift flap is arranged in a set state in which a gap exists between the leading edge flap and the main wing with a gap width of between 0.1% and 0.4% relative to the local wing chord. | 07-07-2011 |
| 20110174933 | SLOT SEAL - A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door. | 07-21-2011 |
| 20110290945 | AIRCRAFT SLAT ASSEMBLY COMPRISING A PLURALITY OF SLATS - An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when the slats are urged into a configurations in which there would be differential extension/retraction of the slats, such as a skewed position. | 12-01-2011 |
| 20110290946 | AIRCRAFT SLAT ASSEMBLY - An aircraft slat assembly comprises a slat, two tracks and two joints, each joint connecting a respective track to the slat. Each track is moveable on a wing structure between a fully extended position and a stowed position. Each joint is arranged to allow relative rotation between the slat and the respective track such that the slat is able to adopt a skewed position in which one track is in the fully extended position and the other track is in the stowed position. | 12-01-2011 |
| 20110297796 | VANE HAVING A REGULATING FLAP AND A GAP COVERING DEVICE AND AN ADJUSTING MECHANISM FOR A GAP COVERING DEVICE - A wing, having an adjustable flap that can be moved between a retracted and an extended setting is provided, as well as a gap-covering device, with an adjustment lever and a gap-covering flap arranged on the latter with a flow surface. The adjustment lever with the gap-covering flap is pre-loaded by means of a pre-loading device into a first setting, in which the gap-covering flap is located in the interior of the wing. The adjustable flap and the adjustment lever with the gap-covering flap are mechanically coupled such that as the adjustable flap moves into its retracted setting, a movement of the adjustment lever takes place against the pre-load effected by the pre-loading device, into a second setting. The flow surface of the gap-covering flap in the second setting of the adjustment lever runs between the upper side of the retracted adjustable flap and the wing flow surface. | 12-08-2011 |
| 20120056038 | 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. | 03-08-2012 |
| 20120074264 | AIRPLANE WING - An airplane wing configuration includes a first wing positioned above and forward of a second wing on an airplane fuselage. The first wing is operable to direct airflow over an upper surface of the second wing, whereby the first and second wings are capable of generating greater lift than a sum of their individual lifts. The first wing may include an adjustable wing flap that redirects airflow over the upper surface of the second wing, and the second wing may include a rotatable portion that pivots to vary the angle of attack of the second wing independent of the first wing. | 03-29-2012 |
| 20120091282 | HIGH LIFT SYSTEM FOR AN AIRCRAFT AND METHOD FOR DETECTING FAULTS IN A HIGH LIFT SYSTEM FOR AN AIRCRAFT - The present invention relates to a high lift system for an aircraft, comprising a flap, which is arranged on a wing box and which can be moved between a retracted position and at least one extended position relative to the wing box by means of a drive device, a support construction, which is arranged on the wing box in the area of the drive device and to which the flap is coupled and which comprises a movable support element, which can be moved to move the flap relative to the wing box, and an acceleration sensor arranged in the area of the flap or the movable support element for detecting accelerations of the flap. | 04-19-2012 |
| 20120091283 | AIRCRAFT CONTROL SURFACE OPERATING DEVICE - An aircraft control surface operating device is provided for operating a control surface on an aircraft body portion to move between a retracted position and an extended position. The aircraft control surface operating device includes a control surface mounting assembly which movably secures the control surface to the aircraft body portion, a drive arm rotatable about a drive axis relative to the aircraft body portion, an actuator for rotating the drive, and a drive link connecting the drive arm to the control surface mounting assembly. The drive link has a control end connected to the control surface mounting assembly and a driven end connected to the drive arm via a drive bearing joint. The drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm is causes extending or retracting movement of the control surface. | 04-19-2012 |
| 20120104178 | CANTILEVERED DIFFERENTIAL MOTION SENSOR AND ASSOCIATED FRAME - The disclosed sensor includes a frame having a base and a plurality of arms integral with the base. The arms are biased to a relaxed position, which may be an extended position. A fuse is fastened between the arms to hold the arms in a non-relaxed position. When incorporated into an aircraft, for example, the disclosed sensor may be connected to a first panel, and a pin connected to a second panel may be positioned between the arms. | 05-03-2012 |
| 20120104179 | AIRCRAFT - The idea of the invention is that the aircraft comprises takeoff and landing wings that are the main aerodynamic elements producing a lift at all stages of takeoff and landing. In cruising flight, the takeoff and landing wings take the flight configuration of a cruise missile to reduce the drag coefficient of the aircraft to a minimum possible and, as a result, save considerable quantities of fuel in the cruising configuration. Each takeoff and landing wing has an invariable cross-section and is provided with two rows of slots to improve resistance to the loss of airflow on the outer surface of the wing. The slots on the outside of the takeoff and landing wing are closed with flaps. This wing design is capable of generating a lift at angles of attack ranging from 1° to 90°. | 05-03-2012 |
| 20120168567 | ELECTRICAL POWER TRANSFER ASSEMBLY - An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion. | 07-05-2012 |
| 20120248256 | Pressure Based Load Measurement - A system and method for a pressure based load measurement system are provided. The system includes two pressure orifices arranged on a top surface and a bottom surface of an airfoil. The pressure differential between these two points is determined and an estimate of the aerodynamic load generated by the airfoil is determined from a linear correlation between pressure differential and load. The location of the orifices may be optimized using analytical or experimental techniques and a least squares empirical curve fit may be used to fit the data collected. | 10-04-2012 |
| 20120292453 | WING ARRANGEMENT COMPRISING AN ADJUSTABLE FLAP AND FAIRING ELEMENT FOR COVERING A FLAP ADJUSTMENT MECHANISM OF A WING - A wing arrangement includes, but is not limited to an adjustable flap, which is adjustable between a retracted position and at least one extended position, has at least one fairing element for covering a flap adjustment mechanism and at least one cover element. The fairing element extends downstream at least as far as the flap and has, in a surface facing the flap, a cutout which correlates with an intended adjustment movement of the flap. The cover element is movably arranged with respect to the fairing element and adapted such to cover the cutout in the fairing element in the retracted position of the flap and expose at least part of said cutout in an extended position. | 11-22-2012 |
| 20120325977 | AIRCRAFT WITH A DEVICE FOR DIRECTIONALLY STABILIZING THE AIRCRAFT, COMPUTER PROGRAM PRODUCT AND METHOD FOR DIRECTIONALLY STABILIZING THE AIRCRAFT - A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a regulating flap adjustment drive of a regulating flap of the same respective airfoil are adjusted in a time segment in such a way that the motion of the spoiler being adjusted and the motion of the regulating flap of the same airfoil deflect in mutually opposite directions in the time segment. The spoiler and the regulating flap are adjusted on the airfoil, on which the adjusted deflections counteract the respectively occurring yawing motion. Also provided are a computer program product for carrying out this method and an aircraft with a directional stabilization device for carrying out this method. | 12-27-2012 |
| 20130009017 | ELECTRONICALLY SYNCHRONIZED FLAP SYSTEM - An electronically-synchronized flap system for a fixed-wing aircraft including a first wing including a first flap panel, the first flap panel being connected with a first in-board actuator and a first out-board actuator, and a second wing including a second flap panel, the second flap panel being connected with a second in-board actuator and a second out-board actuator. In an embodiment, the system can further include an electronic control unit (ECU) configured to control the first and second in-board and out-board actuators to electronically synchronize the positions of the first and second flap panels. | 01-10-2013 |
| 20130020443 | CONNECTING DEVICE, FLAP SYSTEM AND AIRCRAFT HAVING SUCH A CONNECTING DEVICE - The invention pertains to a connecting device for connecting a first structural component and a second structural component that can be moved relative to the first structural component in an articulated fashion such that three rotational degrees of freedom are provided. | 01-24-2013 |
| 20130037658 | AIRCRAFT WITH A CONTROL DEVICE - An aircraft with airfoils having a main wing and at least one control flap arranged such to be adjusted relative to the main wing, as well as a high-lift system with at least one regulating flap for adjusting the lift of the airfoils to adjust the state of lift of the aircraft, featuring flow control devices for influencing the fluid flowing over the surface segment; an activating unit; and a lift state specification device connected to the activating unit for adjusting the state of lift of the aircraft. | 02-14-2013 |
| 20130099061 | FLAP ROLLER ARRANGEMENT, FLAP ASSEMBLY, AND METHOD FOR REMOVING A ROLLER ASSEMBLY FROM A FLAP FITTING - A flap roller arrangement for supporting a flap on a wing of an aircraft is disclosed herein. The flap roller arrangement includes, but is not limited to, a roller assembly that is configured for rolling engagement with a flap track of the wing and for engagement with a flap fitting. The flap roller arrangement further includes a retaining member that is removably coupled to the roller assembly. The roller assembly is configured to egress through an opening in the flap fitting in a direction away from the flap track. The retaining member is configured to obstruct egress of the roller assembly through the opening when the retaining member is coupled to the roller assembly. The roller assembly is enabled to egress through the opening when the retaining member is removed from the roller assembly. | 04-25-2013 |
| 20130099062 | STRUCTURAL ARRANGEMENT, AIRCRAFT OR SPACECRAFT AND METHOD - The present invention pertains inter alia to a structural arrangement, comprising a box structure, a first fibre portion which extends in a first plane, a second fibre portion which extends in a second plane, the first and the second fibre portion being interconnected at a crossing point thereof, the first fibre portion comprising a first portion on one side of the crossing point and a second portion on the other side of the crossing point, the first portion being connected to a first portion of the box structure and the second portion being connected to a second portion of the box structure, the second fibre portion forming, on one side of the crossing point, an inner web inside the box structure and, on the other side of the crossing point, an outer web outside the box structure. | 04-25-2013 |
| 20130214096 | SEAL ASSEMBLY - A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position. | 08-22-2013 |
| 20130256461 | FLAP ARRANGEMENT AND AIRCRAFT WITH AT LEAST ONE FLAP ARRANGEMENT - A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented. | 10-03-2013 |
| 20130277503 | CONTINUOUS MOLDLINE TECHNOLOGY (CMT) ELASTOMERIC CONTROL SURFACE - A continuous moldline technology elastomeric control surface and methods are presented. A control surface is coupled to a fluid-dynamic body. An elastomer interface is coupled to the control surface and the fluid-dynamic body such that a joint gap caused by movement of the control surface relative to the fluid-dynamic body is filled. | 10-24-2013 |
| 20130306801 | ARTICULABLE ROTATIONAL COUPLING FOR AN AIRCRAFT - An airfoil surface control system includes a movable surface. An actuator is coupled to the surface. The airfoil surface control system includes a motor. A torque tube assembly operatively couples the motor and actuator and includes first and second shafts coupled by a universal joint. The universal joint is configured to provide a first maximum angle between the first and second shafts. A stop is configured to provide a second maximum angle between the first and second shafts that is less than the first maximum angle. | 11-21-2013 |
| 20140027580 | HIGH LIFT SYSTEM FOR AN AIRCRAFT - A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor. | 01-30-2014 |
| 20150008292 | FLOW CONTROL STRUCTURE AND ASSOCIATED METHOD FOR CONTROLLING ATTACHMENT WITH A CONTROL SURFACE - A wing assembly, a wing applique and an associated method for controlling the flow of air over a wing are provided. A wing assembly may include a wing having leading and trailing edges. The wing assembly also includes a flow control structure, such as an applique, carried by the surface of the wing so as to extend from a first end to a second end. The flow control structure defines an inlet proximate to the first end, an outlet proximate to the second end and the internal passage extending from the inlet to the outlet. The wing assembly may also include a control surface, such as a wedge, positioned downstream of the outlet. The flow control structure is configured to control the flow of air exiting from the outlet in order to correspondingly control attachment of the air with the control surface. | 01-08-2015 |
| 20150053825 | HIGH-LIFT DEVICE OF AIR VEHICLE - A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed. | 02-26-2015 |
| 20150060607 | LIFT FLAP BEARING APPARATUS, LIFT FLAP ASSEMBLY, AIRFOIL AND AIRCRAFT - A lift flap bearing apparatus is improved with respect to aerodynamics, construction space and assembly, for guiding and adjusting a first lift flap and a second lift flap. The lift flap bearing apparatus comprises a first guiding device for guiding the first lift flap and a second guiding device for guiding the second lift flap. The first and the second guiding devices each have a first curved guide rail and a second curved guide rail. | 03-05-2015 |
| 20150144741 | AERODYNAMIC SEALING MEMBER FOR AIRCRAFT - A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | 05-28-2015 |
| 20150292561 | HYBRID BEARING ASSEMBLY WITH ROLLING ELEMENTS AND PLAIN BEARING - A bearing assembly includes an outer race having an inner surface defining a concave contour and an inner race positioned in the outer race. The inner race has an inner surface defining a bore therethrough and an outer surface defining at least one groove circumscribing the outer surface. A plurality of rolling elements is rollably located in the groove and is in rolling contact with the inner surface of the outer race. A lubricious liner has an inner liner-surface and an exterior liner-surface, the exterior liner-surface being disposed on the inner surface defining the bore. The lubricious liner has a modulus of compression of a magnitude sufficient to allow misalignment of the inner liner-surface relative to the exterior liner-surface in response to a force applied thereto. | 10-15-2015 |
| 20150336658 | BEARING INSTALLED ON AN AIRCRAFT STRUCTURE - An edge flap arrangement for an aircraft wing includes a main flap element and an actuator. A linkage arrangement supports the main flap. The linkage arrangement includes a drop hinge link arrangement. The drop hinge link arrangement includes a fixed strut and a drop link. The fixed strut and the drop link are pivotally connected by a hinge point. The hinge point includes an hourglass bearing. The hourglass bearing includes an inner member, an outer member, and a plurality of hourglass rollers. Any combination of the inner member, the outer member, and the hourglass rollers are fabricated from CREN, Cronidur 30, XD15NW, 422 Stainless Steel, CRES, and/or 440C Stainless Steel. A cage is disposed between the inner member and the outer member. The cage includes a plurality of first rails and a plurality of second rails. Opposing pairs of first rails and second rails define a plurality of pockets. | 11-26-2015 |
| 20150360769 | HIGH LIFT SYSTEM FOR AN AIRCRAFT, AIRCRAFT HAVING A WING AND A HIGH LIFT SYSTEM AND METHOD FOR MOVING A HIGH LIFT SURFACE RELATIVE TO THE WING OF AN AIRCRAFT - A high lift system for an aircraft, comprises a drive unit, a high lift surface, at least one primary drive station, each primary drive station having a shaft connection couplable with the drive unit and a primary lever couplable with the high lift surface. The high lift system further comprises at least one secondary unit, each secondary unit having a secondary lever couplable with the high lift surface. Each one of the at least one primary drive station is adapted for moving the respective primary lever on driving the shaft connection, and each one of the at least one secondary unit comprises a selectively activatable brake, such that the secondary lever follows the motion of the one of the at least one high lift surface when the brake is deactivated. | 12-17-2015 |
| 20160028332 | POSITION AND SPEED SYNCHRONIZATION FOR A DUAL LINEAR ACTUATOR FLAP SYSTEM - A method for controlling a first motor and a second motor to synchronize respective positions of the first motor and the second motor may comprise comparing the positions to determine a position difference, incrementally increasing a speed of one of the first motor and the second motor and incrementally decreasing a speed of the other of the first motor and the second motor according to the position difference, and repeating the incrementally increasing and incrementally decreasing until the respective positions are synchronized. Additionally, motor current limiting may be applied by reducing the target speed of the motor(s) with high applied torque(s), which may result in a position difference between the two motors subject to synchronization/correction. If current limiting is applied to one or both of the motors, speed synchronization may be applied in addition to position-based synchronization. | 01-28-2016 |
| 20160031546 | LIFT-REDUCING APPARATUS FOR AIRCRAFT WINGS - Modern aircraft wings generally have a lower surface the rear part of which is concave over at least some of its length, for additional lift. Sometimes it is desirable to reduce the wing lift, for instance during turbulence. To this end the wing | 02-04-2016 |
| 20160083082 | LINK FOR COUPLING AN AIRCRAFT LIFT DEVICE TO A TRACK - A link for coupling an aircraft lift device to a track that is deployable about an axis of rotation. The link includes a track member to be fixed relative to the track, a lift device member to be fixed relative to the lift device, and an intermediate member that couples the track member to the lift device member. The link is configured to allow for sliding movement of the lift device member relative to the track member such that the lift device is slidable along a linear path relative to the track in a direction of the axis of rotation of the track. | 03-24-2016 |
| 20160144947 | HIGH-LIFT SYSTEM - A high-lift system for an aircraft includes a high-lift flap which is arranged on the wing of the aircraft and is mounted on a carriage coupled to the wing, the carriage being displaceably mounted on a track by means of a high-lift bearing. The high-lift bearing includes a plain bearing. | 05-26-2016 |
| 20170233061 | CONTROL SURFACE ELEMENT FOR AN AIRPLANE | 08-17-2017 |
| 20190144101 | OPEN AND CLOSED CONTROL OF ACTUATORS, WHICH DRIVE AERODYNAMIC CONTROL SURFACES OF AN AIRCRAFT | 05-16-2019 |
