Techniques for drone device control are provided. In one example, a computer-implemented method comprises: meeting, by a drone device operatively coupled to a processor, an aircraft at a first location; and guiding, by the drone device, the aircraft to a second location along a ground movement path selected from a plurality of ground movement paths associated with an airport. The guiding can comprise providing a direction indication to the aircraft; and monitoring a defined region around the aircraft for one or more hazards. The guiding can also comprise, in response to identifying a hazard from the one or more hazards related to the defined region around the aircraft, providing a hazard indication to the aircraft.

There is provided a leading edge system for an aerospace vehicle. The leading edge system has at least one structural member. The leading edge system further has a plurality of removable modules removably attached to the at least one structural member. Each removable module has a hollow box substructure and at least one flange portion disposed along a first end of the hollow box substructure. The leading edge system further has a plurality of first attachment elements configured for attaching the at least one flange portion of the removable module to a first end portion of the at least one structural member. The leading edge system further has a plurality of second attachment elements configured for attaching a second end of the hollow box substructure opposite the flange portion, to a second end portion of the at least one structural member opposite the first end portion.

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.

A method of using a bagged power generation system comprising windbags and water-bags for harnessing wind and water power to produce electricity to meet the escalating energy needs of mankind. Windbags integrated with aerodynamically shaped inflatable bodies filled with lighter-than-air gas: HAV, UAV, airplanes; enabling the apparatus to attain high altitude to capture and entrap high velocity wind. Water-bags integrated with hydrodynamic shaped bodies HUV, UUV, Submarine-boats; enabling the apparatus to dive, capture and entrap swift moving tidal-currents. Attached tether-lines pulling on the rotating reel-drums and generators to produce electricity. Active control surfaces, turbo-fans, propellers provide precision control of the apparatus. A system configured to maximize fluids capture, retention and optimized extraction of its kinetic energy. An extremely scalable and environmentally friendly method, system, apparatus, equipment and techniques configured to produce renewable green energy with high productivity and efficiency.

Embodiments described herein relates to an Unmanned Aerial Vehicle (UAV) having vibration dampening and isolation capabilities, the UAV including a first frame portion, a second frame portion, and a third frame portion. Each of the first frame portion, the second frame portion, and the third frame portion is separated from one another. At least one first support member inelastically coupling the first frame portion and the third frame portion. At least one second support member elastically coupling the second frame portion and one or more of the first frame portion or the third frame portion to isolate the first frame portion and the third frame portion from vibration of the second frame portion.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.