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.

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.

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.

A lightweight flying vehicle includes a carrier body, at least two fan-tube propulsion devices, two steering devices and a flight wing. The fan-tube propulsion devices are respectively disposed at two opposite sides of the carrier body and have a sufficient propulsion force. The steering device is disposed on a moving line of the airflow discharged from the fan-tube propulsion devices and is configured to change a direction of the airflow discharged from the air discharge opening, so that the lightweight flying vehicle is in a high-speed flight mode. The flight wing can provide a lift power in the high-speed flight mode.

An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.

Techniques and architecture are disclosed for a multirotor vehicle having a rotor assembly with a plurality of rotors to provide upward thrust. Attached to the rotor assembly is a frame that includes a frame extension having a first end pivotally attached to the rotor assembly. The extension also includes a second end pivotally attached to a frame body. The vehicle further includes first and second actuators. The first actuator pivots the rotor assembly to position it within a horizontal plane to allow thrust generated by the rotor assembly to lift the vehicle. The second actuator pivots the rotor assembly within the horizontal plane so that thrust generated by the rotor assembly lifts the vehicle. The vehicle also includes a harness connected to the frame and configured to secure an operator's torso to the multirotor vehicle.

A back mounted flight machine comprises a frame comprising a connecting bracket, a pair of lateral arms extending from the connector bracket, and an engine mounted on each of the lateral arms in a selected position. A harness is mounted on the connecting bracket of the frame between the pair of lateral arms. Further, a fastening mechanism is provided for connecting the harness to the connecting bracket to permit relative movement between the harness and the frame in a plurality of orientations.

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.

In an embodiment, a ducted fan propulsion system comprises an outer cowling, adapted to form a duct. The duct houses one or more fan blades rotating about a central axis. One or more motors are in communication with the fan blades and in communication with a power source. The duct is transversed by a plurality of spokes. In an embodiment, multiple ducts are housed within an outer cowling, with each duct comprising one or more rotatable fan blades, one or more central axes, and one or more motors. In each embodiment, one or more members are attached to the ducted or multi-ducted fan propulsion system and extend to a user or vehicle. The members terminate in a handle further comprising a throttle adjuster.

A device includes a harness system configured to be attached to a parachute harness of a parachute. The device also includes a propulsion system connected to the harness system, wherein the propulsion system is configured to be off when undeployed and during freefall, and wherein the propulsion system is configured to deploy during canopy flight stage to generate thrust for a parachutist of the parachute. The device further includes a circuitry configured to control power generation by the propulsion system to control the thrust. The device includes a power source configured to power the circuitry and the propulsion system.