A shock resistant fuselage system includes first and second fuselage side walls, each of the first and second fuselage side walls having a plurality of guide posts, and a printed circuit board (PCB) rigidly attached to at least one of the first and second fuselage side walls, the PCB having a plurality of guide slots, each of the plurality of guide posts slideably seated in a respective one of the plurality of guide slots so that elastic deformation of the PCB is guided by the guide slots between the first and second fuselage side walls.

An airframe is provided that can be flown under the control of an operator or an automated sensor and feedback system. The airframe can be any of a variety of known configurations with multiple rotors, fixed or retractable wings, puller or pusher propellers, or jet engines. The airframe includes at least one arm that is used to intercept and disable another airborne vehicle. In some configurations, the arm is fixed and can include fingers at its outer end. In other configurations, the arm is movable from a closed condition to an open condition. A wire or net is connected between the arm and a portion of the airframe so that the wire or net is spread open when the arm is deployed to the open condition. The wire or net are configured to disable or capture a target such as another aerial vehicle.

An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV having an exterior surface, an aerial vehicle (AV) tab extending from the exterior surface, a tube containing the UAV, the tube including a tab stop configured to controllably hinder travel of the AV tab past the tab stop, and a pair of opposing tab guides configured to position the AV tab for travel over the tab stop.

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 drone docking ports (DDP) mounted on a pole top in close proximity to an accident scene with an openable and closable enclosure, a docking plate having integrated battery wired or wireless recharging pads, and a control module (CM) is disclosed. The CM is adapted to autonomously control all functions of the DDP including actuation of the enclosure and relay of video, audio, and flight control information between the CM and a central monitoring center and/or emergency personnel. A drone with a top and bottom profile design allowing numerous drones to be stacked upon one another and store in the DDP. When the DDP enclosure is in an open position, a drone or stack of drones may initiate a flight from the DDP and to re-dock the drone or stack of drones when the flight is completed, the enclosure may be closed to protect the drone or stack of drones.

A drone docking ports (DDP) mounted on a pole top in close proximity to an accident scene with an openable and closable enclosure, a docking plate having integrated battery wired or wireless recharging pads, and a control module (CM) is disclosed. The CM is adapted to autonomously control all functions of the DDP including actuation of the enclosure and relay of video, audio, and flight control information between the CM and a central monitoring center and/or emergency personnel. A drone with a top and bottom profile design allowing numerous drones to be stacked upon one another and store in the DDP. When the DDP enclosure is in an open position, a drone or stack of drones may initiate a flight from the DDP and to re-dock the drone or stack of drones when the flight is completed, the enclosure may be closed to protect the drone or stack of drones.

An airframe is provided that can be flown under the control of an operator or an automated sensor and feedback system. The airframe can be any of a variety of known configurations with multiple rotors, fixed or retractable wings, puller or pusher propellers, or jet engines. The airframe includes at least one arm that is used to intercept and disable another airborne vehicle. In some configurations, the arm is fixed and can include fingers at its outer end. In other configurations, the arm is movable from a closed condition to an open condition. A wire or net is connected between the arm and a portion of the airframe so that the wire or net is spread open when the arm is deployed to the open condition. The wire or net are configured to disable or capture a target such as another aerial vehicle.

A UAV package delivery system includes a cabinet for deployment inside a merchant facility. The cabinet is configured for storing and charging UAVs on-site at the merchant facility remote from a command and control of the UAVs. The cabinet includes a plurality of cubbies, power circuitry, communication circuitry, and a controller. The cubbies are each sized and shaped to receive one of the UAVs. The power circuitry is configured for charging the UAVs when the UAVs are stowed within the cubbies. The communication circuitry is configured for communicating with the UAVs when the UAVs are proximate to the cabinet or stowed within the cubbies and for communicating with the command and control. The controller causes the UAV package delivery system to retrieve status information from the UAVs, relay the status information to the command and control, and relay mission data between the command and control and the UAVs.

The present disclosure provides a launching mechanism for a drone that is housed within a container. The launching mechanism is also housed within the container and is disposed at the bottom portion of the container such that the effect of its activation causes the drone to move along a container axis defined by the longitudinal axis of the container, at a direction towards a top cover of the container and eject therethrough during the launching process. The launching mechanism includes two elements, each has a receptacle portion, wherein the receptacle portion of one of the elements is received within the receptacle portion of the second element. The two receptacle portions, when one is received within the other, confine an inner space. One of the elements is a static element that is fixed to the container, and the other element is a dynamic element that upon application of force along the container axis in the direction of the top cover is free to move in the force direction and to push the drone that is disposed between it and the top cover of the container. A pressure generator of the launching mechanism is configured for controllably causing an abrupt increase of pressure in the inner space, thus generating a propelling force along the container axis in the direction of the top cover that pushes the drone and causing its launching out of the container. The dynamic element is detachably attached to the static element such that when the propelling force exceeds a certain value, the two elements detach one from the other and the dynamic element continues to move along the container axis.

An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.