Systems and methods for providing a mobility system with modular adaptability. Many embodiments incorporate a number of different electric thrusters that can provide the vertical and horizontal thrust necessary to achieve flight mobility for a given payload. Additionally, many embodiments allow for modular elements to be connected and disconnected for different flight missions such as longer sustained horizontal flight with fixed wing elements. Some embodiments may be adaptable to carry a human payload and controller.

Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.

Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.

An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.

An energy converter that utilizes compressed environmental air includes an air compressing unit, at least one first battery, at least one second battery, a plurality of direct current (DC) accessories. The air compressing unit includes a supply duct, a nozzle duct, a pressurized air tank, a compressor, a power-generating tube, and a plurality of air-flow generators. The compressor is in fluid communication with the supply duct. The pressurized air tank is in fluid communication with the compressor. The nozzle duct is in fluid communication with the pressurized air tank. The power-generating tube is in fluid communication with the pressurized air tank and nozzle duct. The plurality of air-flow generators is operatively coupled within the power-generating tube. The plurality of air-flow generators is electrically connected to the first battery that powers the plurality of DC accessories and is electrically connected to the second battery that powers the compressor via an inverter.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

Aircraft may include electric motors. The aircraft electric motors may include a rotor assembly comprises an outer diameter portion, and inner diameter portion, and an end portion, arranged to define a stator cavity, and a rotor hub configured to connect to a shaft of the aircraft electric machine, a stator assembly arranged within the stator cavity, and at least one fan assembly arranged in the rotor assembly and configured to induce a cooling flow through the stator cavity.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

A peripheral propulsion system having a propulsion unit, an upper section, and a lower section. The propulsion unit has a motor, a motor engagement section, an extension coupled to the motor engagement section, and two or more blades coupled to the extension. The extension is located between the upper section and the lower section. The output section is located about at least a portion of the lower section, and the two or more blades are located outside a periphery of the vehicle. When the motor is running, the two or more blades are capable of drawing fluid from about the periphery of the vehicle and through the output section.