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.

An unmanned aerial vehicle includes at least one rotor motor configured to drive at least one propeller to rotate; a passenger compartment sized to contain a human or animal passenger; and a hybrid generator system configured to provide power to the at least one rotor motor and to generate lift sufficient to carry the human or animal passenger. The hybrid generator system includes a rechargeable battery configured to provide power to the at least one rotor motor; an engine configured to generate mechanical power; and a generator motor coupled to the engine and configured to generate electrical power from the mechanical power generated by the engine.

The invention relates to a device for propelling a passenger, comprising a body arranged to receive said passenger and cooperating with a fuel-fed thrust unit. The arrangement of such a device enables great freedom of movement in the air. More specifically, the thrust unit comprises at least one thrust sub-unit, each advantageously comprising at least two thrusters and secondary course-correction and/attitude-correction thrusters.

The present disclosure concerns a flight system comprising: a controller, a group of one or more propellers coupled to the controller; wherein the controller comprises of one or more sensors; and wherein the controller is configured to: capture data from the one or more sensors; perform an analysis on the data; wherein the analysis is configured to indicate a failure of a propeller; adjust the speed of one or more propellers coupled to the controller based on the analysis indicating the failure of the propeller.

Systems and methods for providing a mobility system with modular adaptability. Many embodiments incorporate a number of different electric thrusters that can provide the vertical and horizontal thrust necessary to achieve flight mobility for a given payload. Additionally, many embodiments allow for modular elements to be connected and disconnected for different flight missions such as longer sustained horizontal flight with fixed wing elements. Some embodiments may be adaptable to carry a human payload and controller.

An innovative capsule type flying vehicle with vertical takeoff and landing, which belongs to the field of devices for air transportation, preferably used for individual transportation, but optionally can be configured for the transportation of two people, where the great inconvenience of products of the same purpose found in the state of technology is the fact that they leave the user exposed and unprotected; differently, the object of this present request consists of a propelled flying vehicle having an aerodynamic envelope and structure, shaped as an ogive capsule, manufactured using light, reliable, safe and easily controllable material, capable of taking off and landing vertically and hovering, flying and maneuvering over great distances and altitudes; consisting of a pod-shaped capsule (1) formed by a base (2), head (3), entry door (4) with a windshield (4A) and a support to fix the propulsion engine.

A method of creating aeronautical lift is described which uses a fast voltage electrostatic force to rapidly simultaneously move the top and bottom surfaces of a lifting device downward, followed by a slow voltage electrostatic force to slowly simultaneously return the top and bottom surfaces to their original positions. This cyclic movement reduces downward air pressure on the top surface of the lifting device and increases air pressure on the bottom surface of the lifting device, thus producing aeronautical lift.

A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled

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 personal propulsion device, including a platform, first and second sensors coupled to the platform to measure at least one of a force or pressure exerted by first and second feet; a first thrust system coupled to the platform to provide thrust in a first direction; a second thrust system coupled to the platform to provide thrust in a second direction that is substantially perpendicular to the first direction; and a controller configured to (i) calculate a difference between a measurement by the first sensor and a measurement by the second sensor, and (ii) adjust an output of the second thrust system based at least in part on the calculated difference.