Abstract: Systems and methods include providing an aircraft with a fuselage having a sliding door system disposed on at least one side of the fuselage. The sliding door system includes a forward sliding door having an upper slide rail and a lower slide rail, a rearward sliding door having an upper slide rail and a lower slide rail, an upper rail coupled to each of the upper slide rail of the forward sliding door and the upper slide rail of the rearward sliding door, a lower rail coupled to each of the lower slide rail of the forward sliding door and the lower slide rail of the rearward sliding door, and a plurality of actuators coupled to each of the upper rail and the lower rail and configured to displace and retract the forward sliding door and the rearward sliding door linearly with respect to the fuselage.

Abstract: An apparatus for launching, recovering, transporting, and storing vehicles is disclosed. The apparatus stabilizes the vehicle while it is in operation or inactive and has a frame connected to at least one stabilizer. In certain configurations, the apparatus stabilizes the vehicle without using the vehicle's onboard landing gear. The apparatus may also include at least one pad connected to the apparatus.

Abstract: A foldable wing with foldable trailing edge flap, that includes a main wing and a foldable trailing edge flap. The main wing includes a wing supporting skeleton and a plurality of skin supporting ribs. The foldable trailing edge flap includes a plurality of crank-shaped flap supporting ribs, a flexible flap skin, a connecting shaft, and a return spring. The plurality of crank-shaped flap supporting ribs are hinged with lower surfaces of corresponding plurality of skin supporting ribs through the connecting shaft to form a foldable trailing edge flap supporting skeleton that relies on the plurality of skin supporting ribs. The return spring makes an upper surface of a long side of each crank-shaped flap supporting rib attach closely to a lower surface of each skin supporting rib. The flexible flap skin is attached to an upper surface of the foldable trailing edge flap supporting skeleton.

Abstract: The invention relates to a flight system having at least two actuated flapping wings (2), an actuated tail unit (9), a control device and an exoskeleton (1) for at least one person. The exoskeleton (1) is movable independently of the flapping wings (2). The control device is configured to receive motion sensor signals from the exoskeleton (1) and to use the motion sensor signals to define specified movement signals and to control the flapping wings (2) and/or the tail unit (9) by way of the specified movement signals. The specified movement signals can be defined such that the movements of the flapping wings (2) and/or of the tail unit (9) follow those of the exoskeleton (1).

Abstract: A system for automated flight correction is an electric aircraft that includes an input control configured to receive a user input and generate a control datum as a function of the user input, at least a sensor connected to the electric aircraft that is configured to detect a status datum and transmit the status datum to a flight controller, a flight controller communicatively connected to the input control and the at least a sensor configured to receive the control datum from the input control, receive the status datum from the flight controller and determine a command datum as a function of the control datum and status datum, and an actuator connected to the flight controller configured to receive the command datum from the flight controller and command at least a flight component as a function of the command datum.

Abstract: A payload loading system is disclosed. The payload loading system includes a UAV and a loading structure. A retractable tether is coupled to a payload coupling apparatus at a distal end and the UAV at a proximate end. A payload is loaded to the UAV by coupling the payload to the payload coupling apparatus. The loading structure of the payload loading system includes a landing platform and a tether guide. The tether guide is coupled to the landing platform and directs the tether as the UAV approaches and travels across at least a portion of the landing platform such that the payload coupling apparatus arrives at a target location. The payload is loaded to the payload coupling apparatus while the payload coupling apparatus is within the target location.

Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible anisotropic skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying active and compliant structures. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.

Abstract: An actuation apparatus for an aerodynamic surface includes a cam track plate having a forward cam track and an aft cam track, a support arm coupled to the leading edge slat panel, the support arm having a forward roller and an aft roller thereon, the forward roller disposed in the forward cam track and the aft roller disposed in the aft cam track, and a bell crank pivotally mounted to the cam track plate, the bell crank having an aft end coupled by an aft link to the wing structure and a forward end coupled by a forward link to the support arm. The forward roller translates within the forward cam track and the aft roller translates within the aft cam track to cause downward rotation of the aerodynamic surface and increased camber of the aerodynamic surface as the aerodynamic surface is extended toward a deployed position.

Abstract: A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

Abstract: Provided is an aerial vehicle, including: a package carrier including a plurality of vertical members being changeable in relative positions in a horizontal direction and surrounding a package in the horizontal direction to prevent falling of the package. A plurality of rotary wings are changeable in relative positions in the horizontal direction. The relative positions of the plurality of vertical members and the relative positions of the plurality of rotary wings are changeable. The package carrier is changed in shape in the horizontal direction in accordance with the relative positions of the plurality of vertical members. The change in the relative positions of the plurality of rotary wings is in conjunction with the shape of the package carrier.

Abstract: An aircraft having a fuselage and a front landing gear; both sides of the rear bottom of the fuselage are fixedly connected with the rear landing gear; one end of the front landing gear is rotatably connected to the front bottom of the fuselage. When the front landing gear rotates to the first position, the second position and the third position, the connecting line between the end of the front landing gear away from the fuselage and the end of the rear landing gear away from the fuselage intersects with the plane, where the fuselage is located, on the side close to the front of the fuselage, parallel to and intersect on the side close to the rear of the fuselage.

Abstract: A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted to a flap support for rotation relative to a wing. A crankshaft assembly is rotatable about an axis and has a crankshaft eccentrically extending between an inboard cylindrical support and an outboard cylindrical support. A coupler link is rotatably engaged to the crankshaft and pivotally connected to the carrier beam. Rotation of the crankshaft from a first eccentric position to a second eccentric position translates the coupler link between a retracted position and a deployed position.

Abstract: A system and method are provided that enable joined materials to expand and contract at different rates while maintaining a structurally sound connection. A system for joining structures with differing coefficients of thermal expansion includes: a first structural element of a first material having a first coefficient of thermal expansion (CTE); a plurality of flexures each defining a first portion and a second portion and attached at the first portion to the first structural element; and a second structural element of a second material having a second CTE, where the second structural element is attached to the second portion of each of the plurality of flexures, where in response to relative movement between the first structural element and the second structural element, the plurality of flexures bend to accommodate the relative movement.

Abstract: In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

Abstract: An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.

Abstract: There is disclosed an emergency door positionable in an exit opening of an aircraft. The door has door supports mountable to the lower wall and each having a pivot point. A first pivot axis is defined between the pivot points. A block is mountable to the lower wall and is offset from a center of the lower wall. A door body is mountable within the opening to the door supporting structure and pivotally mountable to the door supports. The door body is pivotable about the first pivot axis from an initial position in which the door body is within the opening, until the door body is disengaged from the door supports. A bottom portion of the door body abuts against the block to define a removal pivot point. The door body is pivotable about the removal pivot point to remove the door body from the exit opening.

Abstract: A tow bar fitting for towing an aircraft is disclosed. The tow bar fitting includes a mount, a pin support, and a tow pin. The mount includes an upper attachment and a lower attachment for affixing the tow bar fitting to a landing gear of the aircraft. The pin support extends from the mount away from the landing gear. The tow pin is positioned in the pin support such that a tow pin plane that horizontally bisects the tow pin is lower than a mount plane that horizontally bisects the upper attachment and the lower attachment when the aircraft is right-side-up on the ground.

Abstract: An aircraft is equipped with an auxiliary access control barrier (AACB) to prevent access to an area of the aircraft. The AACB includes laterally extendable door panels that are slidably attached to each other to vary a width of the AACB, a hinge by which the door panels are pivotably attached to the aircraft, such that the door panels are pivotable between a deployed position, in which the door panels are positioned across the opening to prevent passage through the opening and in which the AACB has a first width, and a stowed position, in which the door panels are positioned to allow passage through the opening and in which the AACB has a second width, and one or more locks to prevent relative motion between the door panels to fix the width of the AACB and/or to secure the AACB within the opening in the bulkhead.

Abstract: A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust. The assembly comprising a support structure, wherein the support structure is coupled to a dual-mode aircraft. The assembly further comprises a control stick coupled to support structure, wherein the control stick having a length and radius is configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal. The assembly further comprises a first interface device disposed on the control stick configured to receive an interaction and enable a thrust element to spin as a function of the interaction. The assembly further comprises a second interface device, wherein the second interface is configured to receive an interaction and disable the thrust element as a function of the interaction.