| CPC B64C 29/0025 (2013.01) [B64D 27/24 (2013.01); B64D 31/06 (2013.01); B64D 27/026 (2024.01)] | 1 Claim |
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1. 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.
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