Abstract: A system architecture for operation of aircraft flaps. The system architecture includes a first pair of motor drive units, the first pair comprising a first motor drive unit (MD1) and a second motor drive unit (MD3), and a second pair of motor drive units, the second pair comprising a third motor drive unit (MD2) and a fourth motor drive unit (MD4). The system further includes a first plurality of switches connected between the first motor drive unit (MD1) and the second motor drive unit (MD3), the first plurality of switches configured to operate a first electric motor and a second electric motor, and a second plurality of switches connected between the third motor drive unit (MD2) and the fourth motor drive unit (MD4), the second plurality of switches configured to operate a third electric motor and a fourth electric motor.

Abstract: The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.

Abstract: A base station is disclosed for use with an unmanned aerial vehicle (UAV). The base station includes: an enclosure; a cradle that is configured to charge a power source of the UAV during docking with the base station; and a temperature control system that is connected to the cradle and which is configured to vary temperature of the power source of the UAV. The temperature control system includes: a thermoelectric conditioner (TEC); a first air circuit that is thermally connected to the TEC and which is configured to regulate temperature of the TEC; and a second air circuit that is thermally connected to the TEC such that the TEC is located between the first air circuit and the second air circuit. The second air circuit is configured to direct air across the cradle to thereby heat or cool the power source of the UAV when docked with the base station.

Abstract: A system for landing and charging an autonomous unmanned aerial vehicle (UAV) is disclosed. The UAV comprises a set of battery powered rotors to fly through the air. The UAV further comprises a landing peg that projects beneath the body configured to be received by a socket of a corresponding landing base. The landing base can have a funnel top to make landing easier. The landing peg has a set of power transfer means that connect with power transfer means in the landing base to recharge the batteries of the UAV. The UAV can be guided to land in the landing base by a ring of LEDs on the landing base.

Abstract: The invention relates to an aircraft seat assembly (14a; 14b; 14c; 14d) comprising at least one aircraft seat device (46a; 46b; 46c; 46d) and at least one additional aircraft seat device (48a; 48b; 48c; 48d) which are arranged at least partly next to one another in at least one common column of seats (36a; 36b; 36c; 36d) and each of which can be adjusted between a sitting position and a lying position. According to the invention, the lying direction (64a; 64b; 64c; 64d) of the at least one aircraft seat device (46a; 46b; 46c; 46d) is oriented in the opposite direction to another lying direction (96a; 96b; 96c; 96d) of the at least one other aircraft seat device (48a; 48b; 48c; 48d).

Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU). The SPU is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines are operable normally and off, respectively, with electrical power generated by the SPU being diverted to the electric motor of the second hybrid-electric engine.

Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.

Abstract: The technology described herein relates to autonomous aerial vehicle rotor configurations. In some embodiments, the aerial vehicle includes a central body that extends along a longitudinal axis from a forward end to an aft end including a port side opposite a starboard side. Multiple rotor arms each have a proximal end coupled to the central body and a rotor assembly arranged at a distal end to provide propulsion for the aerial vehicle. The rotor assemblies include a first set of rotor assemblies and a second set of rotor assemblies. The first set of rotor assemblies are arranged in a non-inverted configuration on a top side of the aerial vehicle such that each rotor assembly includes an upward-facing rotor. The second set of rotor assemblies are arranged in an inverted configuration on a bottom side of the aerial vehicle such that each rotor assembly includes a downward-facing rotor.

Abstract: An aircraft wing is disclosed including a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. An inductive coupler is arranged to inductively transmit data and/or power between the main wing element and the movable wing tip device. The inductive coupler removes the need for wires and cables to pass across a joint between the main wing element and a movable wing tip device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to transmit data and/or power between the main wing element and the movable wing tip device.

Abstract: Described are crossbeam assemblies for installing a furnishing to a passenger compartment. The crossbeam assemblies can include a first structural member configured to span two floor-mounted channels in a passenger compartment, and at least two attachment elements that are slidingly connected with the first structural member. The attachment elements are repositionable along the first structural member to mate with the floor-mounted channels, and lockable to retain the first structural member with respect to the two floor-mounted channels when the first structural member is attached.

Abstract: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

Abstract: A drone docking station for a vehicle includes: a transfer device configured to have a cargo loaded on a drone or to vertically move the cargo transferred by the drone; a guide device including a guide panel provided on a roof of the vehicle and connected to an upper end portion of the transfer device to have the drone accommodated on an upper portion of the guide panel, wherein the guide panel is disposed to surround the transfer device and provided to move inward or outward or to be rotated around a center portion of the transfer device; and a control unit electrically connected to the guide device and configured to rotate or move the guide panel so that the drone corresponds to the cargo positioned in the transfer device when the drone is accommodated on the guide panel.

Abstract: According to at least one example a launch system is provided, including a carrier vehicle and at least one payload vehicle. The payload vehicle includes a payload propulsion system and aerodynamic lift surfaces designed for providing the payload vehicle with aerodynamic powered flight at a design subsonic cruise speed at a desired altitude. The carrier vehicle is configured for carrying the at least one payload vehicle at least up to the desired altitude, and further includes a solid rocket propulsion system for propelling the launch system to the desired altitude. The carrier vehicle is configured for providing a predetermined forward speed at the desired altitude, correlated to the design subsonic cruise speed. The carrier vehicle is configured for releasing the payload vehicle with respect to the carrier vehicle at the desired altitude and the predetermined forward speed. The design subsonic cruise speed is less than 0.7 Mach number, and, the desired altitude is greater than 3 km.

Abstract: Separation device assemblies are provided. The assemblies include a plurality of first segment elements, each first segment element having an attachment portion and a frangible portion, the attachment portion of the first segment elements is arranged to fixedly connect to a first structural component and at least one second segment element having an attachment portion and a securing portion, wherein the attachment portion of the at least one second segment element is arranged to fixedly connect to a second structural component. At least two of the plurality of first segment elements are attached to the at least one second segment element adjacent to each other and a first segment joint is formed between adjacent first segment elements. An expansion device cavity is formed between the attached first and second segment elements.

Abstract: A compact and lightweight, drone delivery device propelled by an electric ducted air propulsion system. The device is called an ArcSpear Electric Jet Drone System and is relatively difficult to track in flight (stealth), relatively fast, able to maneuver quickly, and able to be re-deployed after recharging and replenishing the payload. The system includes a frame carrying the propulsion system, payload, and controls. The frame structure supports a flight controller and a ducted turbine system with at least one and preferably four turbines the blades/impellers being secured inside a protection shroud/duct and individual electric motors that are powered by rechargeable batteries.

Abstract: Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

Abstract: Unmanned aerial vehicles including wing capture devices and related methods are disclosed. An example unmanned aerial vehicle includes a fuselage and a wing assembly, the wing assembly including a shoulder coupled to the fuselage, the shoulder including a joint, the joint distal to the fuselage, a wing coupled to the joint, and a hook, the hook coupled to the shoulder, the hook including a groove to receive a cable to arrest flight of the unmanned aerial vehicle.

Abstract: Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

Abstract: A release system for the release of satellites from a launch vehicle is provided that includes: (i) a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; (ii) at least one launch arm extending perpendicularly from the torsion bar and comprising (a) a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and (b) a guide having a first end connected to a second end of the torsion lever, and a second free end; (iii) at least one slider which is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; and (iv) and a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

Abstract: A multi-modal robot capable of legged and aerial locomotion includes a body structure including a plurality of legs, each leg having at least one joint; a plurality of thrusters connected to the body structure; and a plurality of actuators for controlled movement of the legs and thrusters. The plurality of actuators are embedded within composite housing structures in the body structure. The composite housing structures are formed by additive printing of composite material over components of the actuators. The composite housing structures are reinforced by layers of continuous carbon fiber material. A method of constructing an actuator for use in a multi-modal robot is also disclosed. Additionally, a computer-implemented method is disclosed to identify particular locations and sizes of components in multi-modal robots providing the lowest total cost of transport.