Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Abstract: A vertical takeoff and landing aircraft includes a starboard wing, a port wing, first and second tilt rotors coupled to the port and starboard wings respectively, and first and second batteries. A pair of control surfaces are arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface. A first flight actuator is electrically connected to the first battery and a second flight actuator is electrically connected to the second battery. The first and second flight actuators are mechanically connected to the first and second control surfaces respectively.

Abstract: The power system can include: a plurality of batteries, a plurality of electric propulsion units, flight computers, and power connections. The propulsion assemblies can include a motor, a propeller, and one or more inverters. The power system can optionally include a plurality of flight actuators. However, the power system can include any other suitable set of components. The power system functions to provide aircraft propulsion and/or aircraft control authority during flight.

Abstract: A hybrid power distribution system for an aircraft includes a first and second set of electrically-powered devices, such as inverters, motors and so forth. A first battery system is coupled to one or more of the first set of electrically-powered devices and a first fuel cell is coupled to one or more of the first set of electrically-powered devices. A second battery system is coupled to one or more of the second set of electrically-powered devices and a second fuel cell coupled to one or more of the second set of electrically-powered devices. The fuel cells and batteries together supply power to the electrically-powered devices as needed, while the fuel cells also keep the batteries charged.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Abstract: An electric motor comprises a rotor and a stator having a yoke. The yoke includes a plurality of teeth mounted to the yoke and being aligned substantially parallel to an axis of rotation of the motor, each tooth including a first radial end adjacent to the yoke and a second radial end extending from the yoke, a plurality of field coils, each field coil being wrapped around a tooth, and a coolant circulation path including a first coolant channel defined between adjacent field coils and a second coolant channel defined between adjacent field coils and between the first radial ends of adjacent teeth. A third coolant channel may be defined between adjacent field coils and between the second radial ends of adjacent teeth.

Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An aircraft propulsion unit includes an electric motor, at least one accessory unit used for operating the electric motor, an inverter module, the inverter module including a plurality of inverters for powering the electric motor and the at least one accessory unit, and a cooling system coupled to the electric motor and the inverter module, the cooling system comprising a coolant path for circulating a coolant through or adjacent to the electric motor and the at least one accessory unit.

Abstract: An electric motor comprises a rotor and a stator having a yoke. The yoke includes a plurality of teeth mounted to the yoke and being aligned substantially parallel to an axis of rotation of the motor, each tooth including a first radial end adjacent to the yoke and a second radial end extending from the yoke, a plurality of field coils, each field coil being wrapped around a tooth, and a coolant circulation path including a first coolant channel defined between adjacent field coils and a second coolant channel defined between adjacent field coils and between the first radial ends of adjacent teeth. A third coolant channel may be defined between adjacent field coils and between the second radial ends of adjacent teeth.

Abstract: A fault-tolerant command and control system including a plurality of flight devices, a plurality of flight computers, a distribution network including a plurality of switches and cables connecting the plurality of flight devices to the plurality of flight computers, and a power source connected to the distribution network.

Abstract: The power system can include: a plurality of batteries, a plurality of electric propulsion units, flight computers, and power connections. The propulsion assemblies can include a motor, a propeller, and one or more inverters. The power system can optionally include a plurality of flight actuators. However, the power system can include any other suitable set of components. The power system functions to provide aircraft propulsion and/or aircraft control authority during flight.

Abstract: A fault-tolerant command and control system including a plurality of flight devices, a plurality of flight computers, a distribution network including a plurality of switches and cables connecting the plurality of flight devices to the plurality of flight computers, and a power source connected to the distribution network.

Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.