Disclosed is a recovery device for unmanned aerial vehicles including a recovery pulley, a pulley rail and a damper, wherein the recovery pulley is used to be coupled for recovering unmanned aerial vehicles, and the pulley rail is used to carry the recovery pulley; the recovery pulley is connected to the pulley rail by rollers, and the damper is connected to the recovery pulley for generating a damping force for a linear movement of the recovery pulley. The recovery device for unmanned aerial vehicles of the present invention can be adapted to recover all types of aerial vehicles, has a simple structure, is easy to manufacture and has a low cost. Through the cooperation of the pulley rail, the recovery pulley and the damper, the recovery of the unmanned aerial vehicles of various weights can be performed. Through the foldable and retractable pulley rail, the recovery device is highly mobile. The present invention can have a wide range of application, and can be applied for comprehensive recovery in ships, vehicles, onboard situations, islands, forests and buildings.

Embodiments relate to aircraft arresting systems that use a net or a cable that extends across a section of a runway. Ends of the net or cable are secured to an elongated tape, which is secured to and forms a part of an energy absorbing brake system. The elongated tape is secured around a tape reel and is allowed to reel out (or “pay out”) once the aircraft is engaged. Described is a system for adjusting the height of the tape such that its elevation can be altered between the point at which it leaves the energy absorbing brake system and when it reaches the aircraft runway.

An example of a drone includes a drone chassis, a plurality of motors attached to the drone chassis and a plurality of propellers coupled to the plurality of motors. The drone further includes a net assembly mounted to the drone chassis. The net assembly extends above the plurality of propellers. The net assembly including a bottom portion and a plurality of upright frame members that are mounted to the bottom portion by a plurality of articulating joints.

Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods are described. A representative system includes a first, carrier aircraft having an airframe, a propulsion system carried by the airframe and positioned to support the carrier aircraft in hover, and a capture line carried by the carrier aircraft and deployable to hang from the carrier aircraft. The capture line is sized to releasably engage with a capture device of a second, carried aircraft. The system further includes a retrieval device positioned to support the carried aircraft for detachment from the capture line.

Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative system includes a first, carrier aircraft having an airframe a propulsion system carried by the airframe and positioned to support the carrier aircraft in hover, and a capture line carried by the carrier aircraft and deployable to hang from the carrier aircraft. The capture line is sized to releasably engage with a capture device of a second, carried aircraft. The system further includes a retrieval device positioned to support the carried aircraft for detachment from the capture line.

An apparatus for use as part of, or attached to, an unmanned aerial vehicle (UAV) to intercept and entangle a threat unmanned aerial vehicle, includes a flight and payload control system for controlling power to the UAV and for controlling maneuvering of the UAV. A host-side mount may be coupled to the UAV and is in communication with the flight and payload control system. A payload-side mount is removably attached to the host-side mount and includes a power interface and a control interface between the payload-side mount and the host-side mount. A counter-UAV system is coupled to the payload-side mount and includes a deployable chute net having a cross-sectional area sized for intercepting and entangling the threat unmanned aerial vehicle; and a deployment mechanism for mounting to the unmanned aerial vehicle.

A UAV recovery system. The UAV recovery system may comprise: a mast having a mast pulley with a swivel, a base, upper and lower booms extending somewhat horizontally from the mast, a cable and pulley arrangement, a shock absorber, and a mast cable coupled between the mast pulley and the shock absorber. The cable and pulley arrangement may comprise: upper boom pulleys coupled near an associated end of the upper boom, lower boom pulleys coupled near an associated end of the lower boom, and a cable forming a loop around the upper and lower boom pulleys. The cable and pulley arrangement may also comprise a net for capturing the UAV. The shock absorber may urge the mast to rotate into a neutral position, but permit the mast to rotate not more than a controlled-tensioned position.

Apparatus and methods for controlling an aircraft and/or a vehicle are described. A vehicle speed and direction are received. A wind-over-vehicle speed and direction of wind at the vehicle are measured. An aircraft ground speed and direction are received. An aircraft-relative-to-vehicle speed and an aircraft-relative-to-vehicle direction are calculated based on the aircraft ground speed and direction and the wind-over-vehicle speed and direction. A wind-over-vehicle envelope is calculated based on system design limits for retrieving the aircraft at the vehicle. The wind-over-vehicle envelope maps limits of wind-over-vehicle speeds over a range of directions that enable retrieval of the aircraft at the vehicle. The aircraft and/or the vehicle are controlled using the wind-over-vehicle envelope, the aircraft-relative-to-vehicle speed, and/or the aircraft-relative-to-vehicle direction.

Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

A containment apparatus and a method for installing the same is provided. The containment apparatus includes a plurality of panels, each of which extends along a height and comprises a panel perimeter including a plurality of perimeter portions, and a panel interior disposed within the panel perimeter. The plurality of perimeter portions includes an attachment border, a coil border, and a set of opposing side portions, which define a respective panel width therebetween. When the containment apparatus is in the installed position, the attachment border of a respective panel is operatively attached to the roof of a structure, such that the plurality of panels and at least one of the exterior walls of the structure cooperate to define a periphery of an unmanned aerial vehicle (UAV) containment area. The UAV containment area defines a controlled environment, directly adjacent to the structure, within which UAV may operate to inspect the structure.