An electric aircraft comprising: an airframe; a power source (208,402); an electric propulsion system configured to move the electric aircraft, the electric propulsion system comprising a group of electric motors (214,412-418) and a group of propellers; an energy-harvesting system configured to recharge the power source (208,402), the energy-harvesting system comprising the group of electric motors (214,412-418) and the group of propellers, wherein each electric motor (214,412-418) comprises a motor controller, a voltage controller, a power inverter, and a motor, the power inverter being connected to the motor, and the voltage controller being connected to the power inverter and the power source (208,402), the motor controller being configured to send commands to the voltage controller and the power inverter; and a controller (210,400) configured to: identify a state for the electric aircraft, the state being selected from one of an operating state and a recharge state; identify a group of recharging parameters for the group of electric motors (214,412-418) based on the state for the electric aircraft; recharge the power source (208,402) for the electric aircraft using the group of recharging parameters to control recharging of the power source (208,402) with the group of electric motors (214,412-418) when a recharge state is present for the electric aircraft; and control a group of motor controllers, each of the motor controllers being configured to: control the voltage controller to regulate the voltage applied to an electric motor in an operating state and regulate the voltage applied to the power source (208,402) during the recharge state; and control the power inverter to send current to the motor of the electric motor when the electric motor is in the operating state and to receive current from the motor when the electric motor is in the recharge state. an airframe; a power source (208,402); an electric propulsion system configured to move the electric aircraft, the electric propulsion system comprising a group of electric motors (214,412-418) and a group of propellers; an energy-harvesting system configured to recharge the power source (208,402), the energy-harvesting system comprising the group of electric motors (214,412-418) and the group of propellers, wherein each electric motor (214,412-418) comprises a motor controller, a voltage controller, a power inverter, and a motor, the power inverter being connected to the motor, and the voltage controller being connected to the power inverter and the power source (208,402), the motor controller being configured to send commands to the voltage controller and the power inverter; and a controller (210,400) configured to: identify a state for the electric aircraft, the state being selected from one of an operating state and a recharge state; identify a group of recharging parameters for the group of electric motors (214,412-418) based on the state for the electric aircraft; recharge the power source (208,402) for the electric aircraft using the group of recharging parameters to control recharging of the power source (208,402) with the group of electric motors (214,412-418) when a recharge state is present for the electric aircraft; and control a group of motor controllers, each of the motor controllers being configured to: control the voltage controller to regulate the voltage applied to an electric motor in an operating state and regulate the voltage applied to the power source (208,402) during the recharge state; and control the power inverter to send current to the motor of the electric motor when the electric motor is in the operating state and to receive current from the motor when the electric motor is in the recharge state. identify a state for the electric aircraft, the state being selected from one of an operating state and a recharge state; identify a group of recharging parameters for the group of electric motors (214,412-418) based on the state for the electric aircraft; recharge the power source (208,402) for the electric aircraft using the group of recharging parameters to control recharging of the power source (208,402) with the group of electric motors (214,412-418) when a recharge state is present for the electric aircraft; and control a group of motor controllers, each of the motor controllers being configured to: control the voltage controller to regulate the voltage applied to an electric motor in an operating state and regulate the voltage applied to the power source (208,402) during the recharge state; and control the power inverter to send current to the motor of the electric motor when the electric motor is in the operating state and to receive current from the motor when the electric motor is in the recharge state. control the voltage controller to regulate the voltage applied to an electric motor in an operating state and regulate the voltage applied to the power source (208,402) during the recharge state; and control the power inverter to send current to the motor of the electric motor when the electric motor is in the operating state and to receive current from the motor when the electric motor is in the recharge state.