An unmanned aerial vehicle includes an atmospheric sensor configured to measure an atmospheric condition. The unmanned aerial vehicle includes a rotor motor configured to drive rotation of a propeller of the unmanned aerial vehicle. The unmanned aerial vehicle includes a hybrid energy generation system including a rechargeable battery configured to provide electrical energy to the rotor motor; an engine configured to generate mechanical energy; and a generator coupled to the engine and configured to generate electrical energy from the mechanical energy generated by the engine, the electrical energy generated by the generator being provided to at least one of the rechargeable battery and the rotor motor.

A vertical take-off and landing aircraft using a hybrid electric propulsion system includes an engine, a generator that produces electric power using power supplied by the engine, and a battery that stores the produced electric power. A motor receives the electric power stored in the battery and electric power produced by the generator but not stored in the battery and provides the power to a thrust generating apparatus. A controller selects either silence mode or normal mode, and determines the amount of electric power stored in the battery and the amount of electric power not stored in the battery from the electric power supplied to the motor. In the silence mode, the controller supplies only the electric power stored in the battery and controls a duration by adjusting output power of motor. In the normal mode, the controller supplies electric power not stored in the battery.

An unmanned aerial vehicle includes at least one rotor motor configured to drive at least one propeller to rotate. The unmanned aerial vehicle includes a data center including a processor; a data storage component; and a wireless communications component. The unmanned aerial vehicle includes a hybrid generator system configured to provide power to the at least one rotor motor and to the data center, the hybrid generator system including 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 data center may include an intelligent data management module configured to control power distribution and execution of mission tasks in response to available power generation and mission task priorities.

An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.

A propulsion system for an aircraft includes a turbomachine having a first turbine, a primary fan mechanically driven by the first turbine of the turbomachine, and an electric generator mechanically driven by the first turbine of the turbomachine. The propulsion system also includes an electric fan assembly, the electric generator electrically connected to the electric fan assembly for powering the electric fan assembly.

A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.

An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.

An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system. The second power drive sub-system is configured to provide a second power to the rotor a second power drive sub-system connected in parallel to the first power drive sub-system and configured to provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor.

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.