An apparatus that detects a tilt, lean, movement and/or rotation and/or change in tilt, lean, position and/or rotation of a user, rider, and/or payload which may use sensors configured to accomplish this detection, where sensors may be on, embedded in and/or attached to a structural device, strap, and/or surface of a vehicle, structure or system, where an apparatus of the present invention may be on, part of, in, attached to or connected to a vehicle, structure or system where detecting, measuring and/or determining a lean, tilt, movement and/or rotation or change thereof, of a user, rider, and/or payload, may be desirable; position or movement and/or center of mass or change thereof may be calculated, or detected; calculations, measurements, metrics or detections from the present invention may be an output or the only output of an apparatus that is an embodiment of the present invention.

A disclosed device allows a person to fly. A disclosed wearable flight system includes a plurality of propulsion assemblies including a left-hand propulsion assembly configured to be worn on a user's left hand and/or forearm and a right-hand propulsion assembly configured to be worn on a user's right hand and/or forearm. A further embodiment includes a body propulsion device that is configured to provide a net force along an axis defining a net body propulsion vector and a support device configured to support a user's waist or torso. The support device is configured to hold a user's body relative to the body propulsion device such that a line extending between center the of the user's head and the center of the user's waist extends, relative to the orientation of the net body propulsion vector during use, by a body propulsion elevation angle that is greater than zero.

A flying vehicle with a battery pack associated with each propulsion module, not centrally located, that is plug and play, meaning it can be easily removed by hand and swapped with any other battery of same model and serial number and used within a propulsion module to power the propulsion system. The system includes battery management modules for monitoring battery pack voltage and evenly re-distributes power across all independent battery packs keeping each pack within relative voltage of each other. The packs within the vehicle are monitored for balancing so one pack cannot become too low in power as to not operate while the vehicle's other packs are still working.

Variations of an aerial vehicle, all with capability of vertical take-off and landing (VTOL), with one variation comprising at least three engines, at least three rotors, a flight control system, battery, and propulsion system. The second VTOL aerial vehicle variation being a hybrid with engine-powered rotors and electric-powered rotors configured to work with a flight control system and battery. The first and second variations having the option of a genset system which recharges the battery. The third VTOL aerial vehicle variation being all-electric-powered rotors configured to work with a flight control system and a genset system which powers the rotors and/or recharges the battery.

A system includes a first battery in a vehicle. The vehicle is capable of being coupled at least temporarily with a second, removable battery and is powered by at least one of the first or the second battery. The system also includes a controller in the vehicle which is configured to estimate an amount of travel-related charge based at least in part on a pickup and drop off location. It is decided whether to charge the first battery using the second battery based at least in part on the amount of travel-related charge and a measured amount of stored charge in the second battery. If it is decided to do so, the first battery is charged using the second battery.

The invention relates to a flight system having at least two actuated flapping wings (2), an actuated tail unit (9), a control device and an exoskeleton (1) for at least one person. The exoskeleton (1) is movable independently of the flapping wings (2). The control device is configured to receive motion sensor signals from the exoskeleton (1) and to use the motion sensor signals to define specified movement signals and to control the flapping wings (2) and/or the tail unit (9) by way of the specified movement signals. The specified movement signals can be defined such that the movements of the flapping wings (2) and/or of the tail unit (9) follow those of the exoskeleton (1).

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 an optical sensor. The rotors are coupled to the airframe and configured to support the UAV in hover. The optical sensor is coupled to the airframe and configured to monitor a position of the UAV within a surrounding environment.

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.

A propulsion device has a body including a platform and a thrust unit, the thrust unit including a first thermal thruster configured to eject a gaseous flow along an axis normal to the platform, the body of the propulsion device including support means of the thrust unit, wherein said thrust unit includes a first electrical secondary thruster configured to correct the attitude of the propulsion device.

A blower including: a forward end; an aft end located opposite the forward end; a shaft located at the aft end; a flange located at the forward end; an internal surface defining an axial passageway within the blower; an external surface radially outward of the internal surface; one or more radial passageway formed within the flange and fluidly connected to the axial passageway, the radial passageway extending from the internal surface to the external surface; and a plurality of blower blades located within the flange and defining the radial passageway.