Abstract: A gliding sports apparatus, which is preferably controllable by upper body and/or arms and/or hands and/or fingers, extends from a leading edge to a trailing edge in an intended direction of overflow when it is fastened to a user. The gliding sports apparatus comprises at least two shoulder ribs which extend substantially from the leading edge to the trailing edge, and wherein each of the shoulder ribs is connectable fixedly to an upper arm of the user but is rotatable about the axis of the upper arm, two hand ribs which extend substantially from the leading edge to the trailing edge, and wherein each of the hand ribs is connectable fixedly to a hand of the user, a back airfoil which is formed between the two shoulder ribs, and two arm airfoils, which are formed in each case between a shoulder rib and a hand rib.

Abstract: An aircraft having a retractable landing gear assembly configured to support some of the weight of the aircraft via one or more wheels, and another retractable non-wheeled landing gear assembly or device configured to support some of the weight of the aircraft via one or more “low-friction” supports such as an air cushion is disclosed. The aircraft may have a maximum take-off weight between 100 and 150 tonnes. There may be two main landing gears each carrying two wheels, a nose landing gear, and a central non-wheeled landing gear providing the low friction vertical support when the aircraft is moving on the ground/operating surface.

Abstract: The 3D extension linkage 100 can include at least one arm that includes two elements connected by a joint. The linkage can include an actuation mechanism, additional arms and/or each arm can include more than two elements, tie rods and/or cross pieces connecting two or more arms, and any other suitable components. The linkage 100 functions to translate and rotate a body attached to one end of the arm relative to a primary structure attached to a second end of the arm.

Abstract: An autonomous mobile mechanically deployed spaceport is disclosed to provide a self-leveling stable landing pad for lunar and Martian descending and ascending spacecraft and which alleviates rocket plume blast effects upon surface soils and volatiles during spacecraft descent and ascent. The autonomous mobile mechanically deployed spaceport is a mechanically deployed unfolding flying landing pad to allow spacecraft to land on the Moon and Mars and alleviates rocket plume blast effects upon surface soils and volatiles.

Abstract: An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake.

Abstract: The invention relates to a rudder control assembly (2) for a missile (1), the rudder control assembly (2) comprising: a first actuator (20) connectable to a rudder (16), which first actuator (20) is configured to steer the rudder (16) when connected to the rudder (16); a coupling element (22) for connecting the first actuator (20) to the rudder (16); and a second actuator (24) for locking the rudder (16) in a fixed position, wherein the second actuator (24) comprises a locking element (26), which is configured to lock and unlock the rudder (16) and which locking element (26) also is configured to connect the first actuator (20) with the rudder (16) by means of the coupling element (22) when unlocking the rudder (16). The invention also relates to a missile (1), comprising a rudder control assembly (2). The invention also relates to a method, performed by a control device (100), for testing a first actuator (20) of a rudder control assembly (2) for a missile (1).

Abstract: An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake. The landing gear modules are configured and controllable to differentially deploy downwardly so as to enable countersteering during taxi maneuvers and turns.

Abstract: Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

Abstract: A flying vehicle comprising a wing ship body having a pair of wing spars secured thereto; and a plurality of hinged wing-rib assemblies disposed along each wing spar that allows the wings to be folded against the body of the flying vehicle. A method for folding or collapsing the wings of a wing-in-ground-effect wing ship comprising providing a wing-in-ground-effect wing ship having a pair of wings, and folding the wings toward and against the body of the wing-in-ground-effect wing ship. A fabric covered wing folding assembly including a pair of wings with each wing having a wing spar and covered by a fabric. A plurality of hinged wing-rib assemblies is disposed along each wing spar that allows the wings to be folded against the body of the aircraft. A method is provided for folding or collapsing the wings of an aircraft.

Abstract: In one embodiment, a flight control system is configured to receive one or more pilot inputs intended to effect a particular control outcome for the aircraft, receive one or more current flight parameters of the aircraft, determine whether or not the aircraft is near or in a stall, and if it is determined that the aircraft is near or in a stall, automatically control the aircraft's flight control surfaces in an oscillatory manner that increases the sensitivity of the flight control surfaces and achieves the pilot's intended control outcome.

Abstract: An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

Abstract: An electric actuator device is provided with: an electric actuator body that has a first fulcrum connected to a rudder surface side of an aircraft and a second fulcrum connected to the aircraft body side, and is driven by an electric motor such that the first fulcrum and the second fulcrum can be brought closer together and drawn further apart; a support member for advancing/retracting between a support position at which the support member supports the first fulcrum or the second fulcrum thereunder, and a retracted position at which the support member is retracted from under the first fulcrum or the second fulcrum; and a retention member for retaining the first fulcrum or the second fulcrum when the support member is located in the retracted position.

Abstract: A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

Abstract: A flight control actuator for actuating an aircraft flight control system is provided. The flight control actuator comprises a gearbox, an output shaft attached to the gearbox and an output lever provided on the output shaft. The output lever is declutchable from the output shaft. The output lever includes an inner diameter through which the output shaft passes and at least one indentation in said inner diameter. The output shaft includes a hollow cylindrical member with at least one hole provided at the axial position of the at least one indentation of the output lever.

Abstract: Aircraft wing droop leading edge apparatus and methods are described. An example aircraft includes a wing having a front spar and an outer skin covering the front spar. The outer skin includes a forward portion located forward of the front spar. The forward portion of the outer skin includes a leading edge movable between a neutral position and a drooped position deflected downward relative to the neutral position. The forward portion of the outer skin has a continuous outer mold line when the leading edge is in the drooped position.

Abstract: An airfoil-shaped body having a variable outer shape, comprising: a first skin, defining a suction surface, a second skin, defining a pressure surface and connected to the first skin at least at a leading edge and/or a trailing edge of the airfoil-shaped body, at least one elongate stiffening beam, arranged inside a cavity of the airfoil-shaped body and secured to at least one of said first and second skins, the stiffening beam including at least a first and a second beam section arranged one after the other and a joining member, arranged between end portions of the beam sections and connected thereto, said joining member being adapted to allow relative movement between the beam sections by an elastic deformation; and an actuator that is operationally associated with said elongate stiffening beam, wherein, upon operating the actuator, the first beam section is moved with respect to the second beam section, or vice versa, changing the orientation of the beam sections with respect to each other, which causes a

Abstract: A vortex generator system has at least two vortex generators protrudable from an outer mold line of a vehicle surface at a location upstream of a cavity leading edge of a cavity in the vehicle surface. The vortex generators are spaced apart from each other and oriented such that the vortex generator aft ends are nearer to each than the vortex generator forward ends. The vortex generator lengthwise direction of each one of the vortex generators is oriented at a vortex generator directional angle relative to a direction of an airflow. The vortex generators are configured to generate a pair of counter-rotating vortices when the airflow passes over through or over the vortex generators. The counter-rotating vortices interact to produce a downwash of air away from the cavity that urges the store away from the vehicle as the store exits the cavity.

Abstract: A wireless autopilot system includes an aircraft attachment device having a mounting plate for securement onto a flight control surface of an aircraft, and a flight control device that is hingedly connected to the aircraft attachment device. The flight control device including an airfoil that is connected to the mounting plate, and a steering tab that is connected to the trailing edge of the airfoil. A main body extends outward from the airfoil to function as an anti-flutter counterbalance. A servomotor is connected to the steering tab by an elongated rigid rod, and a controller having a wireless transceiver for communicating with an application on an externally located processor enabled device. Changes in the position of the servomotor during flight are instructed by the application, and result in a change to the orientation of the aircraft.

Abstract: An apparatus for determining a type of a recording medium is provided. A detection unit detects a characteristic value indicating a physical characteristic of a recording medium. A measurement unit measures a moisture content correlated with a moisture content of the recording medium. A determination unit determines the type of the recording medium based on the moisture content and the characteristic value. The determination unit may correct the characteristic value using the moisture content or correct a rule for determining the type of the recording medium using the moisture content unit, and determines the type of the recording medium in accordance with the corrected characteristic value or the corrected rule.

Abstract: A high-lift actuation system for differentially actuating a plurality of high-lift surfaces of an aircraft is disclosed. An exemplary high-lift actuation system includes a centralized drive device for centralized actuation control of an inboard high-lift surface of a first wing and a second wing, respectively, and at least two independent drive devices for individual actuation control of an outboard high-lift surface of the first wing and the second wing, respectively. The centralized drive device may include a central power drive unit (PDU) operably coupled to a common central driveline for driving the inboard high-lift surfaces, and the common central driveline may be separate and spaced apart from a respective driveline of the independent drive devices. The common central driveline may mechanically synchronize movement of the inboard high-lift surfaces, and a controller may electronically coordinate synchronized movement and controlled differential movement of the plurality of high-lift surfaces.