| Entries |
| Document | Title | Date |
|---|
| 20090261204 | SYSTEM AND METHOD FOR VARYING THE POROSITY OF AN AERODYNAMIC SURFACE - A variable porosity system for an aircraft includes a first layer, a second layer and an actuator mechanism. Each of the first and second layers has at least one pore and are slidable relative to one another. The actuator mechanism is operative to move the first and second layers relative to one another such that the pores are movable into and out of at least partial alignment with one another to allow for fluid communication therebetween. At least one of the first and second layers is substantially continuous with an outer mold line surface of an aerodynamic member such as an aircraft wing. The actuator mechanism is configured to modulate the frequency of the opening and closing of the pores with respect to flight conditions of an aircraft. | 10-22-2009 |
| 20110101170 | SHAPE MEMORY ALLOY ACTUATOR - An aircraft system may include an airfoil and a deployable device coupled to the airfoil. The system may further include a shape memory alloy actuator coupled between the airfoil and the deployable device. The actuator may be movable between a first position with the deployable device deployed relative to the airfoil, and a second position with the deployable device stowed relative to the airfoil. The system may additionally include an activatable link positioned between the actuator and the deployable device. The link may have an engaged configuration in which motion of the actuator is transmitted to the deployable device, and a disengaged configuration in which motion of the actuator is not transmitted to the deployable device. | 05-05-2011 |
| 20110101171 | Apparatus for Twisting a Wing to Increase Lift on Aircraft and Other Vehicles - A method and apparatus for varying the twist of a wing such that induced drag is minimized or reduced during cruise and lift is maximized or increased at least during takeoff and landings. In addition, variations in the twist may produce yawing and rolling moments. The twist amount is varied pursuant to the operating conditions, including those parameters used to determine the lift coefficient. The twist for reducing induced drag and/or improving lift may be employed by geometric or aerodynamic twist, including full span control surfaces used to provide roll control, high-lift and reduced induced drag. The twist may also be employed by twisting just a portion of the wing or the entire wing, either geometrically or aerodynamically. | 05-05-2011 |
| 20110101172 | Wing For An Aircraft - The invention pertains to an aerodynamic body that can be adjusted relative to a main wing of an aircraft by means of an adjusting device, wherein a gap between the aerodynamic body and another aerodynamic body or a component of the fuselage or the main wing is formed on one lateral end and the gap is variable due to the adjustability of the aerodynamic body, featuring a gap bridge-over device with a shell part that extends along the gap and overlaps the outer shell of the aerodynamic body in the wingspread direction on the front side thereof in such a way that the shell part can be telescopically moved relative to this aerodynamic body in the wingspread direction; to an airfoil for an aircraft with a main wing and a plurality of aerodynamic bodies that are arranged adjacent to one another transverse to the chord direction; to an airfoil for an aircraft with a main wing and an aerodynamic body that can be adjusted relative to the main wing by means of an adjusting device and is arranged adjacent to a component of the fuselage or the main wing transverse to the chord direction, as well as to an aircraft with such an airfoil. | 05-05-2011 |
| 20120012712 | AIRCRAFT ASSEMBLY AND SPAR - An aircraft assembly comprising: a pair of covers; a spar web extending between the covers in a thickness direction, the spar web having a length which extends in a span-wise direction; and a container which extends from the spar web and houses at least part of a system component. The container comprises first and second side walls which are spaced apart from each other across the spar web in the thickness direction, and inboard and outboard walls which are spaced apart from each other along the spar web in the span-wise direction. The spar web and at least part of the container are integrally formed as a single piece. Typically the assembly is a wing assembly with a fuel tank; a track; a high-lift device carried by the track; an actuation mechanism for moving the track and high-lift device between an extended high-lift position and a retracted low-lift position; and a track container which extends from the spar web into the fuel tank and houses at least part of the track when it is in its retracted low-lift position. The spar web and at least part of the track container are integrally formed as a single piece, typically from a laminar composite material. | 01-19-2012 |
| 20120112011 | CASING FOR A LIFTING AID - A casing for a lifting aid for an aircraft, comprising at least one strake which extends essentially in a protruding manner in the direction of flight in relation to an outer surface of the casing. An aircraft comprising a lifting aid and said type of casing. | 05-10-2012 |
| 20130068894 | WING FOR GENERATING LIFT FROM AN INCIDENT FLOW - The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge. | 03-21-2013 |
| 20130087661 | PROPULSIVE UNIT FOR AN AIRCRAFT - This invention relates to a propulsive unit for an aircraft, comprising: a nacelle which defines a duct for channeling an airflow when in use and which provides an outwardly facing surface of the propulsive unit, the outwardly facing surface having an aerodynamic shape; a fan unit for accelerating the airflow within the duct when in use; wherein the duct has an inlet and an outlet and the nacelle is operable to adjust the either or both of the area of the inlet and outlet whilst substantially retaining the aerodynamic shape of the outwardly facing surface. | 04-11-2013 |
| 20130233976 | WING AND DEVICES THEREFOR - A device and a related method are disclosed for selectively providing a modified aerodynamic flow over a wing under aerodynamic flight conditions with respect to a respective datum aerodynamic flow over an external wing surface of the wing in the absence of the device under similar aerodynamic flight conditions. The device includes a body configured to be movably mounted to the wing for selective displacement between at least two different positions with respect to the external wing surface and having an external body surface. The device includes a motion inducing arrangement coupled to the body and configured for providing the selective displacement. In each position, the body is in a respective superposed relationship with a respective wing surface portion of the wing external surface and the modified aerodynamic flow includes airflow over the external body surface. A wing and an air vehicle including the device are also disclosed. | 09-12-2013 |
| 20130341467 | SWING TIP ASSEMBLY ROTATION JOINT - A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body. | 12-26-2013 |
| 20150097087 | SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE - A swing wing tip system for an air vehicle is provided. The swing wing tip system has a swing wing tip assembly with an unfixed wing tip portion movably connected to a fixed wing portion of a wing. The swing wing tip assembly has a dual load path structure configured to transfer load from the unfixed wing tip portion to the fixed wing portion. The dual load path structure has dual wing skin plates and a rotation joint coupled between the dual wing skin plates and configured to rotationally couple the unfixed wing tip portion to the fixed wing portion. The rotation joint has a dual rotation pin element having a center rotation axis and dual rotation elements configured to rotate about the center rotation axis. The swing wing tip system has an actuator assembly coupled to the rotation joint and a controller system coupled to the actuator assembly. | 04-09-2015 |
| 20150321747 | AIRCRAFT WING AND AN AIRCRAFT COMPRISING SUCH AIRCRAFT WING - An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position. | 11-12-2015 |
| 20150353186 | ACTUATORS FOR FLIGHT CONTROL SURFACES - An actuator assembly includes an actuator body, a ram, and a cross pin. The actuator body has an internal axial cavity bounded by an actuator body wall and defines a pivot axis. A longitudinal slot extends along a portion of the length of the actuator body wall and is in communication with the internal axial cavity. The ram is slidably received within the axial cavity of the actuator body. The cross pin is mounted to the ram and extends laterally from the ram and into the longitudinal slot for converting linear motion of the ram into rotational motion about the pivot axis for displacing a control surface of an air vehicle. | 12-10-2015 |
| 20160167092 | DEVICE AND METHOD FOR ELECTROSTATICALLY CLEANING A SURFACE | 06-16-2016 |
| 20170233059 | AIRFOILS FOR STUNT FLIGHTS | 08-17-2017 |
