According to an aspect of the invention, a method of optimal safe landing area determination for an aircraft includes accessing a probabilistic safe landing area map that includes a plurality of probabilistic indicators of safe landing areas for the aircraft. A processing subsystem that includes one or more processing resources generates a list of candidate safe landing areas based on the probabilistic safe landing area map and one or more constraints. At least two of the candidate safe landing areas are provided to a path planner. The list of candidate safe landing areas is ranked based on results from the path planner indicating an estimated cost to reach each of the candidate safe landing areas. Based on the ranking, an indicator of an optimal safe landing area is output as a desired landing location for the aircraft.

A rotor blade rotation system includes two or more rotor blades, each rotor blade in mechanical communication with a hub and pivotable about an axis of rotation, a bearing plate comprising a rotating portion and a non-rotating portion, a fold linkage coupled to the rotating portion of the bearing plate and in mechanical communication with the rotor blade, and an actuator coupled to the non-rotating portion of the bearing plate and operable to reposition the bearing plate from a first position to a second position such that the folding links pivot the rotor blades from a deployed position to a forward folded position.

An exemplary high-speed hybrid propulsion system for a tiltrotor aircraft includes two pivotal nacelles, each nacelle comprising an electric motor coupled to a proprotor; an electric aircraft system; an electric generator; an electrical bus electrically connected to the electric generator, the electric motors, and the electric aircraft system; and a convertible turbofan engine coupled to an electric generator through a drive shaft.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades. The rotor blades and counter-rotation blades can be folded upward into a storage position. In addition, the unmanned aircraft can have solar panels positioned about the top housing and fuselage of the aircraft.

A protection system for a classroom or other space to protect against a terrorist. The system includes a fixed control unit and a mobile control unit. The fixed control unit contains a hanger for drones to be launched against the terrorist. The fixed control unit also includes data storage units, a computer, a computer program and a memory, power storage units, a sighting laser for obtaining location information about the terrorist and an etching laser for marking the terrorist, an optics system for receiving visual information, and a telecommunication unit to send and receive information. The mobile control unit is worn by a protecting person in the space and includes some of the same components as the fixed control unit. It also has a local aiming system that includes for example a rifle type sight. The drone is a self-contained, self-propelled robotic flying vehicle that can be very small or even the size of a mouse. It has a mag-lev engine, electrical storage units and an aeronautically shaped body.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

In a hybrid flight vehicle, having multiple rotors attached to a frame, a gas turbine engine to drive the rotors; a generator connected to the gas engine to generate electric power, a battery store the electrical power generated by the generator. multiple first electric motors connected to the rotors to drive the same by the electric power supplied from the battery, a second electric motor connected to the gas turbine engine to motor the engine by the electric power supplied from the battery and a control unit to control flight, wherein the control unit stops supply of the fuel to the engine when a detected residual of the battery is equal to or greater than a predetermined value, and supplies electric power to the second electric motor to motor the engine when a detected temperature of the engine is equal to or higher than a predetermined temperature.

In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.

A vertical take-off and landing (VTOL) aircraft is provided and includes wings, first and second nacelles supported on each of the wings, each of the first and second nacelles including a propeller drivable to generate aircraft thrust, and an asymmetrical power generation unit. The asymmetrical power generation unit includes a single engine unit disposed in only one of the first and second nacelles to generate power to drive the propellers of both the first and second nacelles.

A power plant for an aircraft such as a UAV with a gas turbine engine that drives an electric generator to produce electrical power. The electric generator is rotatably supported by two foil bearings. A centrifugal compressor is secured to a forward side of the generator rotor shaft. The centrifugal compressor draws in cooling air that flows through the two foil bearings and between a space formed between the rotor coil and the stator coil of the electric generator to provide for cooling of both foil bearings and the coils of the generator.