Abstract: A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

Abstract: A wing for an aircraft including a fixed wing and a high-lift device movable between a retracted position and an extended position. The high-lift device includes a movable fence. The fence is movable between a first position in which the fence does not protrude beyond an outer surface of the high-lift device and a second position in which the fence protrudes beyond the outer surface of the high-lift device. The fence is in the first position when the high-lift device is in the retracted position and in the second position when the high-lift device is in the extended position. Further, an aircraft with such a wing, a high-lift device and a fence as well as use of a high-lift device and a fence are provided.

Abstract: Provided is an adaptable spoiler for a wind turbine blade, including: a flexible body including: an outer surface to be exposed to air flow; an internal surface limiting a cavity to be inflated with fluid to different level, wherein a shape and/or position and/or orientation of the surface to be exposed to air flow changes upon inflating the cavity to different level.

Abstract: Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

Abstract: A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.

Abstract: Provided is an adaptable spoiler for a wind turbine rotor blade, including: a base element adapted to be connected at or integrated with a rotor blade; an airfoil element being attachable to the base element and having an airfoil shaped surface to be exposed to an air flow.

Abstract: This invention relates to an airfoil modifying device, a wind turbine blade and a method of modifying an airfoil profile of the wind turbine blade. The airfoil modifying device comprises a deformable element connected to a filler element, both configured to deform between a retracted position and an extended position. The airfoil modifying device is passively deformed by the local air pressure acting on the blade surface and thus the airfoil modifying device.

Abstract: A method and an apparatus for monitoring a motorcycle. Based on the acceleration-relevant data, a vehicle motion and a vehicle position in three-dimensional space are estimated. The vehicle position in space is analyzed and is evaluated as a normal or a critical riding state. A detection direction of a sensor unit is predefined in such a way that in an upright normal resting position of the motorcycle the detection direction lies in a horizontal plane, and the detected acceleration-relevant data encompass a first acceleration component in a longitudinal vehicle direction and a second acceleration component in a transverse vehicle direction. A riding state evaluated as critical is plausibilized with the estimated vehicle motion in order to recognize a critical resting position after an accident. An emergency call is generated when a critical resting position after an accident is recognized.

Abstract: A modular flat-packable drone kit includes a plurality of components that can be assembled into a drone. Components of the drone kit include elements that may be cut from a flat sheet of material, thereby enabling low cost manufacturing and compact packaging and may be assembled without specialized tools. A set of drones may operate in a standalone mode or may be coupled together and operated in a group configuration.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: An aircraft having an empennage rotatable about a longitudinal axis via an electric motor drive is disclosed herein. A pair of horizontal stabilizers extend from opposing sides of the rotatable empennage and are independently rotatable via electric motor drives. The rotatable empennage is operable for controlling yaw, pitch and rolling moments without a traditional vertical stabilizer and rudder system which can reduce weight as well as the radar cross section of the aircraft. This technology can also be applied to a weapon control system such missile such as a missile.

Abstract: A flap support fairing system incorporates a fairing attached to a flap and deployed downward with the flap during flap extension. The fairing has an inboard butterfly portion mounted with an inboard hinge and an outboard butterfly portion mounted with in outboard hinge. A fairing deployment mechanism is responsive to flap extension and is configured to rotate the inboard butterfly portion laterally inboard about the inboard hinge relative to an airflow direction and to rotate the outboard butterfly portion laterally outboard about the outboard hinge relative to the airflow direction. Upon flap extension, rotation of the inboard and outboard butterfly portions reduces impingement of a core engine plume on the deployed fairing.

Abstract: Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

Abstract: Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

Abstract: An aircraft engine nacelle spoiler assembly including a number of spoilers and actuators. Each spoiler has a drag surface and a nacelle connection point. The spoilers are shiftable via the actuators between a stowed position and a deployed position such that the drag surfaces are substantially parallel with the direction of relative wind when the spoilers are stowed and exposed to the relative wind when the spoilers are deployed.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: An aerodynamic structure for an aircraft including a first region having a first magnetic sealing surface, movably connected to a second region having a second magnetic sealing surface. The structure is moveable between a first configuration in which the first sealing surface contacts the second sealing surface such that the first region and the second region form a continuous aerodynamic surface, and a second configuration in which a gap exists between the first and second magnetic sealing surfaces and. The magnetic sealing surfaces are configured such that an attractive magnetic force exists between the magnetic sealing surfaces in the first configuration. The aerodynamic structure is configured such that during movement between the first and second configurations, relative movement of the first and second regions occurs along a direction at an angle in the range 1-90° to the normal of the first sealing surface and/or the second sealing surface.

Abstract: Systems and methods for aerially delivering cargo into a body of water while avoiding parachute entrapment and entanglement are described. The system includes a parachute having a canopy and suspension lines. The system further includes a weight coupled to a first end of the suspension lines and a ring that is configured to float in the body of water. The weight is coupled to the cargo, and the ring is disposed between the weight and the canopy with the suspension lines passing through the center of the ring.

Abstract: A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

Abstract: A process and a machine for improving a performance of a particular model of an aircraft, via reducing a size of a horizontal stabilizer for the particular model of the aircraft, the process comprising augmenting a nose-up moment, for the particular aircraft model, provided by a reduced horizontal stabilizer for the particular aircraft model, via addition of an ailevatoron mixer.

Abstract: In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Abstract: An aircraft wheel fairing drag device, which increases the functionality and operating capabilities of an aircraft wheel fairing for a fixed landing gear aircraft, has a linear actuator, a drag door, and a mounting plate. The mounting plate is positioned within the aircraft wheel fairing and supports the linear actuator. Meanwhile, the linear actuator is operably coupled to the drag door, wherein a driver linearly positions a push rod that is pivotally engaged with a rod mount of the drag door. The rod mount and a fairing hinge are connected to a drag pane, wherein the rod mount is operably disposed from the fairing hinge to allow the drag pane to be angularly positioned relative to the aircraft wheel fairing as the push rod is linearly extended. The fairing hinge provides a rotational axis between the aircraft wheel fairing and the drag pane about which the drag pane is rotated.

Abstract: A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.

Abstract: A machine for packaging articles includes a frame; a feeder feeding film to a packaging station to wrap articles. A sealing unit includes at least two sealing elements movable relative to each other between a spaced-apart position and a close-together position where the two sealing elements cooperate to seal the film interposed between them. First and second mechanisms having first and second motors move the sealing unit. The second motor is operatively coupled to at least one of the two sealing elements. The first and/or the second mechanisms include at least one articulated arm, respectively. A control unit is operatively connected to the first motor and to the second motor to drive them in proper relationship to move the two sealing elements relative to each other and relative to the frame according to a predetermined law of motion.

Abstract: A system for emergency crew return and down-mass orbit comprising a stowable, self-contained, deployable maneuvering reentry vehicle for automated, on-demand reentry to ground for cargo of 1-10 kilograms or up to single or multiple human use for evacuation of orbital facilities. The system includes a deployable “aeroshell” that is contiguous (a single geometric object—surface or hollow shape—that can morph in 3D shape), modular (a collection of modular components externally acting as a contiguous shape, but morphed in 3D via actuators contained in each modular member to create a general asymmetric geometry), or discontiguous (a collection of independently controlled surfaces or bodies that morph to form desirable asymmetric drag configurations).

Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.

Abstract: The present invention provides an aircraft including: a main wing; and a flight control surface that is deployed from the main wing in a first direction and in a second direction different from the first direction. In the aircraft, an end surface of the flight control surface facing the main wing when the flight control surface is not deployed is inclined with respect to the first direction or the second direction on at least one side of a longitudinal direction of the flight control surface, and a portion of the main wing facing the end surface is also inclined with respect to the first direction or the second direction in accordance with the end surface.

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Abstract: An aerodynamic lifting device comprises a chassis (200); a rotor (120) having a rotational axis (R) and a plurality of rotor blades (123) disposed in an annular ring about the rotational axis (R) supported by the chassis (200); and a torque transmission means (126,130,139) to provide tractive force for rotating the rotor (120). The torque transmission means (126,130,139) co-operates with at least one complementary and circumferentially extending drive surface (126a, 126b) of the rotor (120) to transmit tractive force as tangential forces and resultant torque sufficient to drive the rotor (120) and thereby generate lift. The aerodynamic lifting device may be used in airborne craft which may be deployed for waterborne use with a buoyant chassis (200), especially of toroidal shape, for elevating the rotor (120) above a water surface (300) during take off and landing.

Abstract: Provided is an inflatable wing for a rotary-wing aircraft capable of obtaining auxiliary lift by inflating the inflatable wing equipped on the fuselage when a main rotor is in non-powered rotation state by not providing power for rotating the main rotor due to causes such as an engine failure in a conventional type of rotary-wing aircraft having a single engine, thereby providing a safer emergency landing.

Abstract: An aircraft ejection system is provided. The aircraft ejection system may comprise a seat, a bridle coupled to the seat, suspension lines coupled to the bridle, and a drogue canopy coupled to the suspension lines. A first side of the drogue canopy may have a lower drag than a second side of the drogue canopy. The first side may comprise a mesh portion and/or an opening to reduce drag. The first side may further include a low-resistance structure with a circular or rectangular geometry. The bridle and the suspension lines may be configured to direct the first side in a predetermined direction, such as downward.

Abstract: A missile defense system on an aircraft for destroying threats to the aircraft. The defense system includes at least one miniature guided missile mounted in a launch tube on the aircraft, where the guided missile includes a target acquisition and seeker system. The system also includes at least one sensor on the aircraft for acquiring a target threat, and a controller on the aircraft receiving signals from the at least one sensor. The controller generates a fire control solution that is provided to the at least one guided missile that directs the guided missile once it is fired from the launch tube towards the target threat, and the seeker system on the guided missile acquires the target once it is launched from the aircraft so as to destroy the target.

Abstract: The present invention provides a drive system which can automatically deploy a ground spoiler even when a wheel is locked. A drive system for a ground spoiler deploys closed ground spoilers 4A to 4D when a wheel speed VW exceeds a wheel reference speed VW1 or when an air speed VB exceeds an air reference speed VB1 after a main gear 6 touches down. The system may also close the deployed ground spoilers 4A to 4D when the wheel speed VW is smaller than a wheel reference speed VW2 or when the air speed VB is smaller than an air reference speed VB2.

Abstract: An apparatus for energy recovery of an aircraft, an aircraft comprising the apparatus and a method of energy recovery are disclosed. The apparatus comprises a turbine having a body and rotor blades. The turbine is adapted to be mounted to the exterior of an aircraft, such that the body receives an air stream flowing at the exterior of the aircraft. The rotor blades are selectively movable between a stowed position and a deployed position, wherein at the deployed position the rotor blades are rotated by the air stream so as to generate electricity. The blades may be deployed during descent of the aircraft to recover energy normally irretrievably dissipated as the aircraft descends and slows. The blades are stowed when not in use, such as during take-off and cruise.

Abstract: 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.

Abstract: A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed.

Abstract: An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.

Abstract: An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction.

Abstract: In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy produced and a step of utilization of such energy to drive a propeller which generates a force opposing the forward motion of the vehicle. Energy is produced by using the displacement of the vehicle with respect to air using a propeller driving a generator, or using the displacement with respect to the ground, using wheels driving a generator, or using generators driven by motors of the vehicle. The energy can be stored in the pneumatic, electric or kinetic form and the generation and driving means are selected according to the technology used for the storage means.

Abstract: A speed brake for aircraft in the form of a flap is provided. The flap can be extended into the air stream for increasing the flow resistance of the air. An extension is attached on the upper side of the flap on one side with respect to the center line of the flap, and the extension is attached in such a manner that in the retracted state of the flap, the extension extends along the flow direction of the air.

Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.

Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.

Abstract: A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.

Abstract: 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.

Abstract: A spin-stabilized projectile is steered by taking air from an air intake at the front of the projectile, and expelling the air along an outer surface of the projectile to alter its trajectory toward the desired impact location. Air taken in through the air intake is directed toward a rotor that is able to rotate relative to the rest of the projectile. The rotor has an outlet that may direct the air taken in at the air inlet out in a direction having both radial and circumferential components. The force produced in the radial direction provides a steering force substantially normal to the projectile axis, used to steer the projectile. The force produced in the circumferential direction is used to provide impetus to spin the rotor. A brake is used to control the rotational speed of the rotor, to control the direction that the air is expelled from the projectile.

Abstract: An aircraft comprises an airbrake which is disposed upstream in front of a vertical tail and which can be swung out into the airflow approaching the vertical tail. In order to reduce structure dynamic loads on the vertical tail, passages are formed in the brake flap.

Abstract: A speed brake for aircraft in the form of a flap is provided. The flap can be extended into the air stream for increasing the flow resistance of the air. An extension is attached on the upper side of the flap on one side with respect to the center line of the flap, and the extension is attached in such a manner that in the retracted state of the flap, the extension extends along the flow direction of the air.

Abstract: System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris.

Abstract: A vehicle may include a vehicle body maneuverable onto a near collision course with a target and a plurality of inflatable ballutes which, when inflated, extend generally radially from the vehicle body. A controller may cause the ballutes to be inflated prior to an anticipated time of collision with the target. A plurality of explosive charges may be attached to at least some of the ballutes. A detonation controller may be coupled to the controller and to the plurality of explosive charges.

Abstract: A system for loading and unloading a cargo assembly onto and from an aircraft. The system comprises an aircraft and a movable platform. The aircraft comprises a forward fairing, an aft fairing, a spine disposed between the forward fairing and the aft fairing and a plurality of mounts coupled to the spine and configured to structurally engage the cargo container onto the spine. The aft fairing is movable between a fixed position for flight and an open position for at least loading and unloading of the cargo assembly. The aircraft is configured such that an unobstructed passageway is provided in an area underneath the spine during loading or unloading of the cargo assembly. An aft access is provided when the aft fairing is moved to the open position. The movable platform is used to maneuver the cargo assembly for loading and unloading onto and from the spine, respectively.