An aerial craft and sealed force vectoring flight system is disclosed. The aerial craft includes a main body hull, lift jets, a generator, an electrical re-introduction circuit, a hydraulic pump, air flow compressors, an RPM sensor, a max speed limiter hydraulic draft by-pass valve, and a battery. The electrical re-introduction circuit throttles the generator into high-velocity rotation and yields excess electrical current to then be applied to the lift jets. The hydraulic pump pulls pressurized hydraulic fluid across a preceding hydraulic drive impellor such that the pressurized hydraulic fluid returns to confinement under pneumatic pressure faster than a discharge of hydraulic fluid. The air flow compressors generate electricity that is re-introduced into the lift electric motors. The RPM sensor and max speed limiter hydraulic draft by-pass valve speed regulate the generator. The battery initially powers the generator.

Provided includes the main body part 100 in which a number of rotors 101 controlled by the control unit 110 are installed on the outside, a number of wing bodies 200 in which the elastic member 220 is opened to both sides to absorb the impact in the event of a collision with the guide 210 placed on the outer side of the rotor 101, a parachute deployment unit 300 installed on the upper side of the main body part 100 and ejecting the parachute canopy 320 upward in an emergency situation, a lower airbag ejection unit 400 installed under the main body part 100 and inflating the lower airbag 401 downward in an emergency situation, and a landing gear unit 500 installed under the main body part 100.

Provided includes the main body part 100 in which a number of rotors 101 controlled by the control unit 110 are installed on the outside, a number of wing bodies 200 in which the elastic member 220 is opened to both sides to absorb the impact in the event of a collision with the guide 210 placed on the outer side of the rotor 101, a parachute deployment unit 300 installed on the upper side of the main body part 100 and ejecting the parachute canopy 320 upward in an emergency situation, a lower airbag ejection unit 400 installed under the main body part 100 and inflating the lower airbag 401 downward in an emergency situation, and a landing gear unit 500 installed under the main body part 100.

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.

This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears.

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.

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.

Drones with propulsions systems supported in a housing are provided where the orientation of the housing is independent from the orientation of the propulsion system. Drones are provided where a propulsion system is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the propulsion system to assume substantially any position with a sphere. Drones are provided where a bladeless inner tube is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the inner tube to assume substantially any position within a sphere. Drone systems are provided with connectable unit drones. An unmanned land vehicle is provided having a wheel assembly that is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the wheel assembly to assume substantially any position with a sphere.

A re-usable intercept drone (104) comprises an elongate fuselage (200), a first wing (202) and a second wing (206) operably coupled to the elongate fuselage (200) and extending substantially away from the elongate fuselage (200). A first propulsion unit (210) and a second propulsion unit (212) are operably coupled to the first wing (202) and the second wing (206), respectively. A third propulsion unit (214) and a fourth propulsion unit (218) are operably coupled to the fuselage (200). The first, second, third and fourth propulsion units (210, 212, 214, 218) are circumferentially spaced about the elongate fuselage (200).