A water-propelled or water-powered unmanned aerial vehicle including a base configured to carry a payload, and at least one nozzle attached thereto. The at least one nozzle is configured to selectively receive pressurized fluid from a source located remotely from the vehicle. The vehicle includes a control system configured to alter or otherwise selectively dictate the flow of fluid through the at least one nozzle and/or the orientation of the at least one nozzle with respect to the base in response to a received control signal for providing controlled unmanned vehicle flight.

A hydraulically propelled drone is provided for delivering firefighting fluid to an elevated location. The drone comprises a housing having a primary inlet configured to receive the distal end of a fire hose, a primary outlet configured to receive the inlet end of a primary nozzle, a central passageway configured to conduct fluid from the primary inlet to the primary outlet, and at least one secondary outlet communicating with the central passageway. At least one lift nozzle communicates with the secondary outlet and is configured to direct fluid in a generally downward direction so as to produce an upward thrust on the drone housing, and at least one valve is contained within the housing and configured to control the flow of said fluid through the primary nozzle and the at least one lift nozzle nozzle.

An unmanned aerial vehicle (UAV) powered using electric propulsion is provided. The unmanned aerial vehicle (UAV) includes a main frame and a plurality of thrust rings. The plurality of thrust rings is arranged in a first spatial configuration around the main frame and is rotatably coupled to at least one actuator in the main frame along a pivot axis. The unmanned aerial vehicle (UAV) further includes a plurality of plasma actuators disposed on at least one of the plurality of thrust rings. Further, in an actuated state, the plurality of plasma actuators actuates to generate a plasma thrust that causes the unmanned aerial vehicle (UAV) to orient along a particular axis or move in a specific direction.

An unmanned aerial vehicle (UAV) powered using electric propulsion is provided. The unmanned aerial vehicle (UAV) includes a main frame and a plurality of thrust rings. The plurality of thrust rings is arranged in a first spatial configuration around the main frame and is rotatably coupled to at least one actuator in the main frame along a pivot axis. The unmanned aerial vehicle (UAV) further includes a plurality of plasma actuators disposed on at least one of the plurality of thrust rings. Further, in an actuated state, the plurality of plasma actuators actuates to generate a plasma thrust that causes the unmanned aerial vehicle (UAV) to orient along a particular axis or move in a specific direction.

A propulsion system, comprising: a fan blade housing; a plurality of fan blades within the fan blade housing; one or more rows of permanent magnets, affixed to the outside of the fan blade housing; one or more fan blade bearings; one or more magnetic field generators affixed to the one or more fan blade bearings and corresponding to the one or more rows of permanent magnets, the magnetic field generators configured to cause the permanent magnets to be propelled forward in the same direction, thereby causing the fan blade housing to which they are attached, and the fan blades within, to spin.

A propulsion system, comprising: a fan blade housing; a plurality of fan blades within the fan blade housing; one or more rows of permanent magnets, affixed to the outside of the fan blade housing; one or more fan blade bearings; one or more magnetic field generators affixed to the one or more fan blade bearings and corresponding to the one or more rows of permanent magnets, the magnetic field generators configured to cause the permanent magnets to be propelled forward in the same direction, thereby causing the fan blade housing to which they are attached, and the fan blades within, to spin.

A hybrid aerial hydro drone includes a body with a plurality of hydraulic thrusters supported on an outer surface of the body and configured to propel the body in a marine environment. The drone also includes a plurality of rotor arms arranged on the body, each rotor arm comprising a rotor system configured to propel the body in an aerial environment. Each rotor arm is deployably configured between a deployed position in which the rotor systems are extended from the body for aerial traversal, and a folded position in which the arms are hydrodynamically folded behind the body for marine traversal. The body also includes a controller, an energy source, a main ballast chamber and a pump with snorkel for operation of the drone.

A fluid distribution system that uses a hovering distribution device and methods for using such a system are provided. In one example, the system may include a reel that provides a hose for the hovering distribution device. The hovering distribution device receives pressurized fluid from the hose, and includes at least one nozzle configured to distribute the pressurized fluid and provide lift for the hovering distribution device using the pressurized fluid. A control system may be configured to execute a fluid distribution plan by controlling at least one of a position and an orientation of the hovering distribution device in a three dimensional space using a direction of the nozzle.

A fluid distribution system that uses a hovering distribution device and methods for using such a system are provided. In one example, the system may include a reel that provides a hose for the hovering distribution device. The hovering distribution device receives pressurized fluid from the hose, and includes at least one nozzle configured to distribute the pressurized fluid and provide lift for the hovering distribution device using the pressurized fluid. A control system may be configured to execute a fluid distribution plan by controlling at least one of a position and an orientation of the hovering distribution device in a three dimensional space using a direction of the nozzle.

Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.