| CPC B60L 50/61 (2019.02) [B64D 27/10 (2013.01); F02C 9/00 (2013.01); F02K 3/00 (2013.01); H01M 10/425 (2013.01); B60L 2200/10 (2013.01); H01M 2010/4271 (2013.01); H01M 2220/20 (2013.01)] | 6 Claims |
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1. A propulsion system of an aircraft mounted in an airframe of the aircraft, the propulsion system comprising:
a gas turbine element including a compressor and a turbine that rotates integrally with the compressor;
a power generator connected to the gas turbine element through a rotation shaft;
a battery accumulating electric power generated by the power generator;
an electric motor driven by at least one of electric power from the power generator and electric power from the battery;
a propeller driven by the electric motor;
a gas turbine control unit controlling an output of the gas turbine element;
a power generator control unit controlling an amount of generated power of the power generator;
one or more sensors for detecting a flight state of the aircraft;
and
wherein the gas turbine control unit and power generator control unit are configured to control power operating points which are each defined using a torque and a rotation number of the rotation shaft based on the flight state detected by the one or more sensors
and a reference operation line acquired by joining a plurality of power operating points at which an output defined as a product of the torque and the rotation number is constant on an operating point map onto which the power operating points are mapped, and
wherein:
target power operating points to a load after a change in the load for first power operating points that are current power operating points on the operating point map in a case in which a change in the load is detected;
by changing a fuel flow in a range not exceeding a predetermined fuel line using the gas turbine control unit, the gas turbine control unit moves the power operating points of the gas turbine element from the first power operating points present on the reference operation line to second gas turbine power operating points that have the same torques as the target power operating points and, at the same time, the power generator control unit moves power operating points of the power generator from the first power operating points present on the reference operation line to second power generator power operating points that are present on the reference operation line and have the same rotation numbers as the second gas turbine power operating points using the power generator control unit; and
after the power operating points are moved to the second gas turbine power operating points and the second power generator power operating points, the gas turbine control unit moves the power operating points of the gas turbine element from the second gas turbine power operating points to third gas turbine power operating points matching the target power operating points with the torque maintained to be constant, at the same time, the power generator control unit moves the power operating points of the power generator from the second power generator power operating points to third power generator power operating points that are present on the reference operation line and have the same rotation number as the third gas turbine power operating points, and, after the power operating points are moved to the third gas turbine power operating points and the third power generator power operating points, the gas turbine control unit sets the power operating points of the gas turbine element as the target power operating points by maintaining the power operating points for a predetermined time without moving the power operating points from the third gas turbine power operating points and, at the same time, the power generator control unit moves the power operating points of the power generator from the third power generator power operating points to the target power operating points within the predetermined time.
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