A power generation apparatus and method comprises at least one gyroglider rotary wing flying at an altitude above the nap of the earth. A strong and flexible tether, connected to the gyroglider frame is pulled with a force generated by the rotary wing. The force is transmitted to a ground station that converts the comparatively linear motion of the tether being pulled upward with a lifting force. The linear motion is transferred to a rotary motion at the ground station to rotate an electrical generator. The tether is retrieved and re-coiled about a drum by controlling the gyroglider to fly down at a speed and lift force that permit recovery of the gyroglider at a substantially reduced amount of retrieval force compared to the lifting force during payout of the tether. Thus, the net difference in force results in a net gain of energy.

Drone (5) which comprises a plurality of propellers (16) driven by motors (17) supported by at least one structure (18), in which a plurality of converters (15) are arranged around the structure (18) to convert electricity to high voltage in low voltage electricity. The present description also relates to a method of controlling the attitude of the drone (5).

A ground station for an unmanned aerial vehicle (UAV) includes a box assembly, a hatch assembly, and a landing pad assembly. The hatch assembly is pivotably coupled to the box assembly. The landing pad assembly is movably coupled to the box assembly and is movably coupled to the hatch assembly.

Aspects of the disclosure relate to flight termination systems for tethered aerial vehicles having envelopes. For instance, a flight termination system may include a wire heating element arranged in a loop around the balloon envelope and connected to a strain relief connector, the strain relief connector, and an electrical cable connected to the strain relief connector. The electrical cable is configured to provide current to the wire in order to melt envelope material of the envelope and terminate a flight of the aerial vehicle.

A self-propelled payload (SPP) for an aircraft, such as an unmanned aircraft. The SPP includes an independent propulsion unit which is configured to counter the effect of payloads of the aircraft. This improves operational effectiveness of the aircraft.

A suspended aerial vehicle system includes an aerial vehicle with a thruster assembly and a supporting line attached to the aerial vehicle that is capable of supporting at least some of the weight of the aerial vehicle. The supporting line may have an adjustable length which when varied, and in coordination with variations in a thrust characteristic of the aerial vehicle, may change the position of the aerial vehicle. Other aspects are also described and claimed.

A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub.

Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods are disclosed. An example unmanned aerial vehicle (UAV) system includes a lift device, a parachute, and a capture line. The lift device includes a canister. The parachute is stowed in and deployable from the canister. The capture line is attached to the parachute and to a line control device. The capture line is configured to be engaged by a capture device located at an end of a wing of a UAV.

Described herein are systems, methods, and devices for recovering unmanned aerial vehicles (UAVs), such as UAVs that are trapped in an obstacle such as a tree. In particular, a method is described, the method including determining location parameters associated with a trapped UAV; navigating to the proximity of the UAV; determining launching parameters and a target associated with the launch of a launching device; and causing the launch of a launching device towards the target. The launching device may include a tether, such that a user may pull on the tether to dislodge the trapped UAV from the tree.

The present invention relates to wind energy park connected to an electrical grid, having airborne wind energy systems (AWES), e.g. with kites. The wind energy park has an electrical DC network connecting the plurality of AWES and a grid converter unit for converting DC to AC, and transmit AC to the electrical grid. The wind energy park control unit controls the AWES to produce electrical power to the electrical grid by alternating between a power production phase, and a recovery phase so to balance the supply of power to the electrical grid according a demanded setpoint. An advantage is that the grid converter may be smaller, as compared to an AC network, because the power is evened out with the negative power from the AWES being in recovery phase. In this way, the invention stabilizes the grid and has a grid forming capability.