The synchronous machine module includes a synchronous machine and a rotational speed controller for controlling a rotational speed of the synchronous machine, which rotational speed controller has a detector for detecting a variable which is formed by the effective power or is dependent thereon. The rotational speed controller is designed to set the rotational speed of the synchronous machine and/or the time profile thereof as a function of the detected variable and/or its time profile. The vehicle drive has such a synchronous machine module and a power generator, which in order to supply the synchronous machine module is connected thereto. The vehicle is, in particular, an aircraft and has such a vehicle drive and/or such a synchronous machine module.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

The disclosure is directed to drive assemblies for unmanned aerial vehicles (UAVs). Specifically, the disclosure is directed to hybrid drive assembly and control system for UAVs, utilizing indexed belt tension modulation to couple and decouple an electric motor and an internal combustion engine.

A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another.

A hybrid electric vertical takeoff and landing (VTOL) aircraft. The hybrid electric VTOL aircraft generally includes a fuselage, a pair of wings, a pair of booms, a plurality of flight components and a power system. The wings are connected to the fuselage and extend generally laterally therefrom with each wing on either side of the fuselage. Each boom is connected to a respective one of the wings and extends generally longitudinally and parallel to the fuselage. The plurality of flight components is configured to provide thrust to the hybrid electric VTOL aircraft. The power system is configured to power the plurality of flight components and includes at least a fuel tank and a generator, and at least a battery. The at least a fuel tank is mounted to at least one of the booms. The at least a battery configured to power the plurality of flight components.

The disclosure is directed to drive assemblies for unmanned aerial vehicles (UAVs). Specifically, the disclosure is directed to hybrid drive assembly and control system for UAVs, utilizing indexed belt tension modulation to couple and decouple an electric motor and an internal combustion engine.

A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.