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 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: 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: 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: 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: 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: 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: 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: 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.

Abstract: By providing propellers for vertical ascent and descent and for horizontal flight, and a blade for horizontal flight, it is possible to obtain an aerial vehicle capable of high-speed horizontal flight and capable of flying a long distance.

Abstract: A flying vehicle with folding wings that drives well on the ground and flies well in the air; controlled from inside, it changes from automotive to aircraft configuration without the operator needing to get out of the vehicle. The balance point of the vehicle is located midway between the front and back wheels, providing good handling on the road. In the aircraft configuration with wings unfolded, there is a front wing and a back wing. The incidence of the front wing is controllable, enabling the craft to rotate and take off with a center of gravity located well ahead of the rear wheels. The back wing is fitted with foldable vertical stabilizers near its wing tips. In automobile configuration the wings are folded on top of the body; the wings resemble a roof rack with large surfboards on it. Driven wheels provide motive power on the ground; ducted fans provide thrust for air travel. An autopilot system provides stability and navigation aid, particularly in bad weather or poor visibility.

Abstract: The present disclosure discloses a trans-media unmanned aerial vehicle device and a control method thereof. The trans-media unmanned aerial vehicle device includes a housing, and a piston which is arranged in the housing and is capable of moving in a reciprocating manner in the housing; one end of the housing is provided with an opening; several flying wings are uniformly arranged in a circumferential direction of the piston; the flying wings are rotatably connected to a side of the piston facing the opening and are spread or retracted like an umbrella; and under the pushing of the piston, the flying wings can be spread to the outside of the housing and retracted back into the housing.

Abstract: By providing propellers for vertical ascent and descent and for horizontal flight, and a blade for horizontal flight, it is possible to obtain an aerial vehicle capable of high speed horizontal flight and capable of flying a long distance.

Abstract: A surface assembly and related method of constructing a surface assembly are used as part of a landing platform. The surface assembly includes a modular structure having an upper surface with a plurality of discrete elements. Each discrete element has a body of metal material defining at least one anchor aperture for receiving a hook or like anchor device for anchoring a helicopter or other powered light aircraft to the surface assembly. The surface assembly is configured to define an array of the plurality of discrete elements in which at least two of the anchor apertures are provided side-by-side. The body of each discrete element has a periphery, and each anchor aperture of the array is inboard of the periphery of a respective body of a discrete element in the array.

Abstract: Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Abstract: The present application provides an unmanned aerial vehicle (UAV) for a long duration flight. An exemplary UAV may include a UAV body assembly. The UAV may also include a flight control system (FCS) coupled to the UAV body assembly. The UAV may further include a motor coupled to the UAV body assembly at one end and coupled to a propeller at the other end. The FCS is communicatively connected to the motor. A center of gravity (CG) of the UAV is at a point between 21% and 25% of a mean aerodynamic chord (MAC) of the UAV.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, a pair of fixed wings attached to the fuselage, a tail assembly attached to an aft portion of the fuselage and including a pair of stabilizers, a plurality of distributed propulsion units having first propellers that rotate about first rotational axes positioned below the fixed wings, and a plurality of tail propulsion units having second propellers that rotate about second rotational axes each positioned inline with one of the stabilizers. The first propellers are mounted fore of the fixed wings and the second propellers are mounted fore of a corresponding one of the stabilizers. Three or more of the distributed propulsion units are mounted to each of the fixed wings.

Abstract: An unmanned aerial vehicle (UAV) has a multicopter section for flying in air with an attached blower section for generating an air stream for blowing dust off surfaces. A flight controller controls the multicopter section, a blower controller controls the blower section, and a power supply supplies power to the multicopter and blower sections. The flight controller and the blower controller are connected, and the blower controller is adapted to supply blower control commands to the flight controller to compensate for the thrust of the air stream from the blower section by flight control of the multicopter section. The UAV may be enclosed by a protective cage in the form of a meshed polyhedron, wherein the rods of the meshes are elastically connected at the respective nodes.