Abstract: A heater mat for heating an airfoil having a chord, a leading edge, and a trailing edge includes a first zone element configured to heat a first chord-wise segment of the airfoil. The system further includes a second zone element configured to heat a second chord-wise segment of the airfoil that is adjacent to the first chord-wise segment of the airfoil. The system further includes a first zone busbar located at the leading edge of the heater mat and electrically coupled to the first zone element.

Abstract: A hinge is coupled to a first component and a second component. The hinge supports the second component for movement relative to the first component between a closed position covering an opening through the first component and an opened position displaced from the opening. The hinge includes a first bracket coupled to the second component, a second bracket coupled to the first component, a support link coupled to the first and second brackets, and a control link coupled to the first and second brackets. Rotation of the support link relative to the first bracket causes rotation of the first component relative to the second component and relative to the support link.

Abstract: A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

Abstract: One embodiment includes a rotary aircraft, including: a rotary propulsion system; a body; and a pair of wings connected on opposite sides of the body, wherein each of the wings includes a flap rotatably connected to a trailing edge thereof and configured to rotate downward relative to the wing during low speed and stationary flight of the aircraft, and to rotate upward relative to the wing during high-speed flight of the aircraft.

Abstract: The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.

Abstract: Aircraft high-lift device brake apparatus, distributed high-lift device brake systems, and methods of actuating such distributed high-lift device brake systems, where each high-lift device brake apparatus includes an extendable high-lift device, an actuator coupled to the high-lift device that can extend or retract the extendable high-lift device, a torque tube coupled to a remote drive unit so that rotation of the torque tube activates the actuator, and a high-lift device brake that includes, in turn, a brake assembly capable of locking the associated high-lift device in its current position, a torque-based brake activator configured to activate the brake assembly when an applied torque exceeds a predetermined threshold, and a flight control brake activator configured to activate the brake assembly when the flight control brake activator receives an activation signal from the flight control system of the aircraft.

Abstract: A system for flight control of an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control, a pusher component, a lift component and a flight controller. The pilot control is mechanically coupled to the eVTOL aircraft. The pilot control is configured to transmit an input datum. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input datum from the pilot control, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.

Abstract: Vertical take-off/landing and horizontal straight flight aircraft for transportation of passengers, cargo, and/or goods are described herein. The aircraft have increased thrust and flight speed; improved controllability and maneuverability of flight; increased safety of take-off, landing and touchdown of the aircraft; reduction in the weight and size characteristics of aircraft. An aircraft includes redistributed, assembled and interconnected small-sized independently operating electric motors of the main rotors obtained by defragmentation of the propeller-motor group (PMG), spaced from each other and forming a small-sized independently operating PMG located at certain distance from the longitudinal axis of the aircraft, and each small-sized main rotor in each small-sized independently operating PMG is connected to the small-sized independently operating electric motor. The small-sized independently operating PMGs are installed inside the screens, on the beams of the common frame and/or on tubes.

Abstract: A variable camber trim unit comprises a housing, an input gear, and an output gear. The input gear and the output gear are rotatably supported by the housing. The variable camber trim unit is selectively configurable to one of a coupled configuration or a decoupled configuration. When the variable camber trim unit is in the coupled configuration, rotation of the input gear relative to the housing causes rotation of the output gear relative to the housing. When the variable camber trim unit is in the decoupled configuration, rotation of the input gear relative to the housing does not cause rotation of the output gear, and the output gear is rotationally fixed relative to the housing.

Abstract: A variable camber trim unit comprises a housing, an input gear, and an output gear. The input gear and the output gear are rotatably supported by the housing. The variable camber trim unit is selectively configurable to one of a coupled configuration or a decoupled configuration. When the variable camber trim unit is in the coupled configuration, rotation of the input gear relative to the housing causes rotation of the output gear relative to the housing. When the variable camber trim unit is in the decoupled configuration, rotation of the input gear relative to the housing does not cause rotation of the output gear relative to the housing, and the output gear is capable of at least 5° and no more than 15° of rotation relative to the housing.

Abstract: A gear unit for transmitting a rotational force to a rotatable member carrying developer and to which a coupling member is mountable. The gear unit includes a hole portion which opens outwardly in a direction along a rotational axis of the cylinder gear and which has an opening capable of accommodating the spherical portion, a groove portion which continues from the hole portion and which is capable of accommodating the projected portion, and a limiting portion for limiting inward movement of the spherical portion in the direction along the rotational axis of the gear. A closing member is provided for partially covering the opening of the hole portion and mounted to the gear to limit outward movement of the spherical portion in the direction along the rotational axis of the gear. The closing member is constituted by a plurality of independent pieces.

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: Actuation assemblies comprise a track comprising a first roller surface, a second roller surface opposite the first roller surface, and a curved section. Actuation assemblies further comprise a carriage operatively coupled to a flight control surface, a first roller rotatably supported by the carriage and comprising a first-roller rolling surface engaged with the first roller surface, a second roller rotatably supported by the carriage and comprising a second-roller rolling surface engaged with the second roller surface, and an actuator, whose distal end is operatively coupled to the carriage to selectively translate the carriage along the track and thus to selectively translate the first roller along the first roller surface and the second roller along the second roller surface.

Abstract: A truss connected to a structure via a fixed rod end attachment and at least one swing-link attachment. A first beam of the truss is connected to a frame member of the structure via a fixed rod end attachment, which locates the truss relative to the frame of the structure. Remaining beams of the truss to be connected to the frame of the structure are attached via swing-link attachments, which can pivot relative to the beam of the truss and the frame of the structure to allow relative movement between the beam and frame. The relative movement allows the structure to flex without imparting additional loads in the truss or the frame of the structure.

Abstract: An actuation unit (15) for actuating a foldable wing tip portion (9) includes a first housing part (19) including a first attachment device (23) configured for attachment to a fixed wing (5), and a second housing part (21) including a second attachment device (25) configured for attachment to a foldable wing tip portion (9). The second housing part (21) is rotatable about a main axis of rotation (35). The second housing part (21) includes a toothed rack (37) having a concave shape and facing the main axis of rotation (35). A drive pinion (39) is supported at the first housing part (19) and engaging the toothed rack (37) for driving the second housing part (21) rotatingly relative to the first housing part (19). The drive pinion (39) is driven by a coupling arrangement (43) that is configured to be coupled to an output (45) of a motor unit (47).

Abstract: Ice protection systems of aircraft and related methods are disclosed. In one embodiment of the present invention, the system includes a gas-discharge lamp and an electric power source. The gas-discharge lamp is configured to emit infrared radiation toward an inner surface of an aircraft skin. The electric power source is operatively connected to the gas-discharge lamp.

Abstract: An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Abstract: A wing for an airplane has an outer wing end and an inner side of the wing for mounting to the airplane. The outer wing has at least two winglets connected to the wing, including an upstream winglet preceding a downstream winglet in a flight direction of the wing. The first winglet and the second winglet are mutually inclined, as seen against the flight direction, by a relative dihedral angle.

Abstract: Various implementations directed to composite skid member with varying cross-sections are provided. In one implementation, an aircraft landing gear assembly may include two composite skid members configured to contact the ground, where each composite skid member includes a first cross-section and a second cross-section, and where the first cross-section is different than the second cross-section. The aircraft landing gear assembly may also include two cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two composite skid members.