A drone including a front section, a wing structure supported by a rotor located behind the front section, and a propeller at the rear. The wing structure including two wings rotating the rotor, the wing structure being able to move between a flight configuration, in which the rotor is immobile relative to the front section and the propulsion provided by the propeller, and a flight configuration with the wing structure rotating, in which the rotor is rotated relative to the front section, the rotor being connected to the front section with a possibility of orienting its axis of rotation relative thereto in order able to direct the drone in the rotary wing structure configuration by acting on said orientation.

A drone including a front section, a wing structure supported by a rotor located behind the front section, and a propeller at the rear. The wing structure including two wings rotating the rotor, the wing structure being able to move between a flight configuration, in which the rotor is immobile relative to the front section and the propulsion provided by the propeller, and a flight configuration with the wing structure rotating, in which the rotor is rotated relative to the front section, the rotor being connected to the front section with a possibility of orienting its axis of rotation relative thereto in order able to direct the drone in the rotary wing structure configuration by acting on said orientation.

Methods and apparatus to deploy unmanned aerial vehicles (UAVs) by kites are disclosed. An example apparatus to deploy a UAV includes a tether line to support the UAV, a tensioner operatively coupled to the tether line, and a kite operatively coupled to the tether line to support the tether line for deployment of the UAV.

Examples include an apparatus for restraining an aircraft during engine acceleration, the apparatus including: a collet shaft that is configured to attach to the aircraft, a rod that is configured to attach to a runway, and a release mechanism that is configured to restrain the collet shaft to the release mechanism and configured to release the collet shaft in response to the release mechanism receiving an electric current.

Examples include an apparatus for restraining an aircraft during engine acceleration, the apparatus including: a collet shaft that is configured to attach to the aircraft, a rod that is configured to attach to a runway, and a release mechanism that is configured to restrain the collet shaft to the release mechanism and configured to release the collet shaft in response to the release mechanism receiving an electric current.

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.

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.

A UAV launch system including a launch rack mounted at altitude, and housing one or more UAVs, and a ground station. The ground station may activate the UAVs for a high-altitude launch. In a further aspect, the UAVs are configured for a stationary, high-altitude launch, without low altitude launch features. Launching a UAV from a high-altitude (greater than about 30 meters or 100 feet) fixed location like an Aerostat or tall building allows the designer to eliminate much of the functionality required for launching the UAV from low altitude as well as ignore the aerodynamics required to support launch (e.g. near-stall) flight conditions.

A UAV launch system including a launch rack mounted at altitude, and housing one or more UAVs, and a ground station. The ground station may activate the UAVs for a high-altitude launch. In a further aspect, the UAVs are configured for a stationary, high-altitude launch, without low altitude launch features. Launching a UAV from a high-altitude (greater than about 30 meters or 100 feet) fixed location like an Aerostat or tall building allows the designer to eliminate much of the functionality required for launching the UAV from low altitude as well as ignore the aerodynamics required to support launch (e.g. near-stall) flight conditions.

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.