Vertical take-off and landing aircraft using hybrid-electric propulsion system and the control method

A vertical take-off and landing aircraft using a hybrid-electric propulsion system comprising:

• a body having fixed-wings;
• an engine arranged on each fixed wing and configured to generate a power by burning fuel;
• a generator connected to the engine and configured to generate an electric power upon operating the engine, wherein the generator also receives the electric power supplied by a power management unit for starting the engine as a starter, the power management unit configured to manage and provide the electric power;
• a battery management system having a battery, wherein the power management unit is configured to provide the electric power to the battery management system to charge the battery;
• multiple motors arranged on each fixed-wing and configured to receive the electric power from the battery management system;
• a first propeller arranged on each of the multiple motors and configured to be operated by each corresponding motor among the multiple motors;
• a second propeller configured to be operated by the engine;
• a clutch unit positioned between the engine and the second propeller and configured to disconnect or connect the power delivered from the engine to the second propeller;
• a pitch control unit configured to adjust an angle of attack of the second propeller;
• a sensor arranged on the generator connected to the power management unit to generate a first detection value by monitoring the generator;
• a control unit configured to control an operation of the engine, the generator, the multiple motors, the second propeller, and the clutch unit,
• at least one electronic speed control unit configured to control a speed of a corresponding one of the multiple motors according to a command of the control unit;
• and
• a load detection line, which is connected to a power line connected to the at least one electronic speed control unit, detecting a load formed on the power line as a second detection value, wherein the control unit, which is connected to the load detection line, is configured to control an output of the engine based on the second detection value,
• wherein the control unit is configured to control the electric power to the multiple motors from the generator, the power management unit, and the battery management system simultaneously during a vertical take-off and landing of the body, wherein the control unit is configured to control the power connected between the engine and the second propeller during the vertical take-off and landing via the clutch unit, wherein the control unit is configured to determine whether a current power generation produced by the generator is appropriate based on the first detection value,
• wherein the multiple motors are configured to facilitate the first propeller to generate a first thrust in a first direction and the engine is configured to facilitate the second propeller to generate a second thrust in a second direction such that the first direction and the second direction are not identical to each other,
• wherein the pitch control unit is configured to adjust the angle of attack of the second propeller, while the clutch unit connects or disconnects a power transmission between the engine and the second propeller to generate a desired thrust during the vertical take-off and landing of the aircraft.