Abstract: A system, computer readable storage device and method for controlling torque in a hybrid electric vehicle. The method comprises determining a state of charge of an energy storage device, obtaining a reference state of charge, obtaining an error from a difference between the determined state of charge and the reference state of charge; and apportioning torque between a motor and an engine based upon the error. The motor is electrically coupled to the energy storage device and powered by the energy storage device. A state of charge (SOC) correction factor is determined based upon the error. The SOC correction factor is used to adjust a torque ratio of motor to engine torque that is determined for a given torque command.

Abstract: A hydraulic ground propulsion system for an aircraft. The system comprises a wheel, axel, an aircraft power interface device, an electric motor, a hydraulic system, a drive assembly and a controller. The wheel is rotatably coupled to the wheel axel. The aircraft power interface device interfaces an aircraft power source. The electric motor is coupled to the aircraft power interface device and receives power from the aircraft power source through the aircraft power interface device. The hydraulic system is driven by the electric motor. The drive assembly mechanically couples the wheel axel to the hydraulic system. The drive assembly is mechanically driven by the hydraulic system. The drive assembly transfers energy from the hydraulic system to the wheel axel. The controller controls the electric motor and the hydraulic system based upon a pilot torque command.

Abstract: A system, computer readable storage device and method for controlling torque in a hybrid electric vehicle. The method comprises determining a state of charge of an energy storage device, obtaining a reference state of charge, obtaining an error from a difference between the determined state of charge and the reference state of charge; and apportioning torque between a motor and an engine based upon the error. The motor is electrically coupled to the energy storage device and powered by the energy storage device. A state of charge (SOC) correction factor is determined based upon the error. The SOC correction factor is used to adjust a torque ratio of motor to engine torque that is determined for a given torque command.

Abstract: A hydraulic ground propulsion system for an aircraft. The system comprises a wheel, axel, an aircraft power interface device, an electric motor, a hydraulic system, a drive assembly and a controller. The wheel is rotatably coupled to the wheel axel. The aircraft power interface device interfaces an aircraft power source. The electric motor is coupled to the aircraft power interface device and receives power from the aircraft power source through the aircraft power interface device. The hydraulic system is driven by the electric motor. The drive assembly mechanically couples the wheel axel to the hydraulic system. The drive assembly is mechanically driven by the hydraulic system. The drive assembly transfers energy from the hydraulic system to the wheel axel. The controller controls the electric motor and the hydraulic system based upon a pilot torque command.