A droneboarding system is disclosed. The droneboarding system includes an unmanned aerial vehicle (drone) for pulling a droneboarder riding a board over a surface, a harness, a tow handle and a plurality of tension lines. Each tension line is attached to the drone and to either the tow handle or the harness. The tension lines are configured in a manner that provides mechanical control of the flight path of the drone. A remote power supply is adapted to be carried by the droneboarder. One of the tension line carries an electrical conductor from the remote power supply to the drone. The electrical conductor provides electrical power from the remote power supply to the drone.

The Electric Jetpack Device has multiple electric ducted or clustered electric jets to create enough/sufficient controlled thrust with battery power alone. It is a lightweight vertical take-off with the electrical power of rechargeable batteries for a safe, vertical lift off vehicle. It is capable of carrying an average human or equivalent payload and flying for several minutes per charge. Motors and propellers are powered by the batteries and managed through an Electronic Speed Controller and a flight controller. The Flight Controller balances thrust and limits roll from side to side. By moving the control handles connected and mounted to an aluminum frame, the device and craft is directed. The pivots tilt the cluster of jetpacks slightly forward or back. The frame is connected to a harness, in which the pilot is strapped. The craft is modular and can be connected to another craft creating a “quadcopter” set-up.

A jet powered personal flying machine composed of a customizable framework consisting of separate bolt-on parts or sections that can be swapped out or switched, including a base frame containing a plurality of mini jet engines, a shell or fuselage, a fuel tank, a flight computer, a plurality of electronic buttons and controls, a parachute, footstands on both sides for the user to place their feet and a single control stick consisting of a metal or carbon fiber tube attached at the front and center of the base, and protruding upwards and slightly forward from the base frame, of which contains electronic buttons and controls for the user to use in flying the machine.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance.

The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.

Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative method for operating an unmanned aerial vehicle (UAV) system includes directing a first, multi-rotor carrier aircraft to carry a second, carried aircraft aloft, and release the second aircraft for flight, while powering the first aircraft with an on-board battery. The method can further include directing the first aircraft to position a capture line in a flight path of the second aircraft to capture the second aircraft.

The present invention relates to flying scooter comprising a base made of fibreglass, 20 fans with 20 motors connected to a power system with components comprising capacitors, batteries, photovoltaic solar cells, an oxygen generator, a regulator, electronic sensors, and electronic chips. The scooter has a circular front part that includes a display that gives operational levels of the components, and the base has a cavity for the passenger's legs, and a rubber strap for securing the passenger. Manual controls are provided as well as a grip for the controls. The controls are connected to the sensors and electronic chips wirelessly.

A propulsion system includes a duct and a fluid flow generator. The duct has an elongated cavity with an inlet portion and an outlet portion. The fluid flow generator is disposed in the duct. The fluid flow generator configured to receive a fluid to generate an inlet stream through the inlet portion and generate an outlet stream through the outlet portion. The outlet stream is configured to generate thrust for a vehicle on which the fluid flow generator and the duct are mounted, and at least one of the inlet portion or the outlet portion is bent in a circular shape to alter a direction of a corresponding either one of the input stream or the output stream.

A flight vehicle, comprising a frame, the frame having a bottom side configured to receive a user harness; a port wing extending from a port side of the frame and a starboard wing extending from a starboard side of the frame, each wing comprising at least one helium wing bag for containing a wing volume of helium and having a wing port for the passage of fluid in and out of the wing bag; a helium backpack secured to a top side of the frame, the helium backpack comprising an inflatable main helium bag configured for holding a main volume of helium, the main helium bag having a main bag port for the passage of fluid in and out of the main helium bag; at least one pressurized container secured to the frame, the at least one pressurized container being configured to contain liquid helium, and having a container opening for the passage of fluid in and out of the pressurized container; at least one electronic valve coupled to the at least one pressurized container for governing fluid flow through the container opening; and a system of hoses configured to carry a flow of helium, the system of hoses connecting the at least one electronic valve to the main bag port and to the wing ports.

Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative unmanned aerial vehicle (UAV) comprises an airframe, a plurality of rotors, and a capture line. The rotors are coupled to the airframe and configured to support the UAV in hover. The capture line is carried by the UAV and is operatively coupled to an immersible anchor. The immersible anchor is configured to be immersed within a body of water during a capture operation involving the capture line.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.