Abstract: A system for aerial vehicle landing is provided. The system includes a displacement compensation unit and a traction control module. The displacement compensation unit includes a top portion, a bottom portion, and at least one actuators connected to the top portion and the bottom portion, configured to provide a displacement compensated top portion to engage with an aerial vehicle. The traction control module includes a traction generator connected to a tether. Through the tether the aerial vehicle is tractioning toward the top portion of the displacement compensation unit. A method for controlling a system for aerial vehicle landing is also provided.

Abstract: In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.

Abstract: A suspension line assembly for a parachute assembly, comprising a plurality of suspension lines bound together at a confluence, a first riser extending between the confluence and a first attachment location disposed on a first strap, a second riser extending between the confluence and a second attachment location disposed on a second strap and a cradle disposed between the first riser and the second riser.

Abstract: A fractal unmanned aircraft system (200) includes a first module (100), a second module (100) and a third module, (100) each having a top member (120) and a first thruster (130) affixed thereto. Each module (100) is laterally coupled to each other. A fourth module (100) has a bottom that is affixed to the top members (120) of the first module (100), the second module (100) and the third module (100) so as to form a tetrahedral structure. A power source (220) supplies power to the first thrusters (130). A control circuit (222) controls the unmanned aircraft system so as to cause the fractal unmanned aircraft system (200) to fly in a controlled manner.

Abstract: There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.

Abstract: A locking system for fixing at least one transport unit for cargo items in an aircraft. The locking system includes a plurality of locking devices and at least one actuating device. Each locking device has at least one locking element for fixing and releasing the transport unit at least one predetermined position and is displaceable in a displacement direction between a fixing position and a release position. The at least one actuating device has at least one actuating unit for initiating an actuating movement and at least one sliding unit for displacing the locking element. The actuating unit is connected to the sliding unit for transmitting the actuating movement by means of at least one transmission section extending transversely to the displacement direction. The sliding unit is mechanically coupled to the locking element to transmit the actuating movement and to move the locking element between the fixing position and the release position.

Abstract: Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

Abstract: An insulation application assembly for applying insulation to a power line employs an open-ended enclosure to partly surround a segment of the power line. The assembly employs an insulation material conveying mechanism to move insulation material from insulation storage to the insulation material applicator connected to the interior surface of the open-ended enclosure.

Abstract: End effectors and systems may capture, release, and/or create a mating engagement between the end effector and a target object. Said end effectors are tolerant of positional and rotational misalignment of the target object, and include a plurality of roller wheels, one or more of which is arranged in a non-parallel plane with respect to one or more other roller wheels. A first roller wheel configured to rotate in a first plane, a second roller wheel configured to rotate in a second plane, and a third roller wheel configured to rotate in a third plane may be arranged such that the end effector is configured to engage a passive receptacle of the target object, to capture the target object. Rotating the roller wheels in the opposite direction may cause the target object to be released or launched, by urging the passive receptacle off of or away from the roller wheels.

Abstract: A locking system includes a locking element which is movable between a first, locking position and a second unlocking position and an unlocking actuator for moving the locking element (from the first position to the second position over an unlocking stroke length (Su). The system further comprises a control unit configured to command the unlocking actuator to move the locking element from the first position to a third position over an anti-icing stroke length (Sa) which is shorter than the unlocking stroke length (Su).

Abstract: An unmanned aerial vehicle according to the present invention includes: a main body; an arm that extends from the main body to support a rotor; a first electrical conductor which is supported by the arm and to which a voltage is applied; a second electrical conductor which is supported by the arm and spaced apart from the first electrical conductor and to which a voltage lower than the voltage applied to the first electrical conductor is applied; and a controller configured to control electrical supply to the first and second electrical conductors.

Abstract: An improved inflatable wing and kit including an inflatable airframe, a center strut connectable to the airframe, a wing panel connectable to the airframe and to the center strut, and a handle. The handle may have first and second ends, each configured to removably connect to the center strut via connection devices on the center strut which are configured to receive the first and second ends of the handle.

Abstract: A rotating wing aircraft 1 comprises: at least one rotor blade 2; a primary gas-flow production means 7 for providing a flow of gas in an internal passage 13 of the at least one rotor blade 2; and a reserve gas-flow production means 11 for providing a flow of gas in the internal passage 13 of the at least one rotor blade 2.

Abstract: A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

Abstract: The present disclosure is directed to a missile having a main body and an articulating nosecone connected to the main body. An actuation system is operable for moving the nosecone relative to the main body via one or more electric motors and associated components. A central aperture is formed through electric motors and the associated components between the main body and the nosecone. One or more cables for transmitting electrical power, sensor data, control signals and the like extend through the central aperture between the main body and the nosecone to provide means for controlling the actuation system.

Abstract: A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.

Abstract: An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

Abstract: An unmanned aerial vehicle (UAV) system energized by power lines includes a UAV, a charging mechanism and an electric circuit. The charging mechanism is operatively coupled to a body of the UAV. The charging mechanism can connect to power transmission lines deployed near an air space in which the UAV is airborne and operating. The charging mechanism can draw power from the power transmission lines to power a flight of the UAV. The electric circuit is onboard the UAV. The electric circuit can generate charging currents based on the power drawn from the power transmission lines to power the flight of the UAV while the UAV is airborne.

Abstract: The present invention concerns a method for launching a payload (3) by means of an arrangement (1), which is configured for storing and launching a payload (3). A launch compartment (5) of the arrangement (1) is configured to eject the payload (3) from the launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1). An air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17).

Abstract: An assembly and a method for manufacturing an assembly for transmitting torque to an aircraft actuator. The assembly and method include a torque tube having a longitudinal axis and an end fitting. The ending fitting includes a connector portion and an engagement portion that is inserted into the torque tube. The engagement portion includes a first end adjacent the connector portion, a second end opposite the first end, and a coupling region between the first and second end that includes an outer coupling surface having an outer diameter and a continuous groove formed thereon. The continuous groove includes two axial grooves that extend along the outer coupling surface along the longitudinal axis and a first parallel groove that extends circumferentially about the longitudinal axis along the outer coupling surface that joins the two axial grooves.