US 12,320,306 B2
Electricity generation system and aircraft
Hiroshi Kobayashi, Tokyo (JP); Ryuji Iijima, Tokyo (JP); Shunsuke Noguchi, Tokyo (JP); and Akira Nishizawa, Tokyo (JP)
Assigned to JAPAN AEROSPACE EXPLORATION AGENCY, Tokyo (JP)
Appl. No. 18/292,047
Filed by JAPAN AEROSPACE EXPLORATION AGENCY, Tokyo (JP)
PCT Filed Jul. 19, 2022, PCT No. PCT/JP2022/028032
§ 371(c)(1), (2) Date Jan. 25, 2024,
PCT Pub. No. WO2023/013398, PCT Pub. Date Feb. 9, 2023.
Claims priority of application No. 2021-127866 (JP), filed on Aug. 4, 2021.
Prior Publication US 2024/0337221 A1, Oct. 10, 2024
Int. Cl. F02C 9/28 (2006.01); F02C 9/32 (2006.01)
CPC F02C 9/28 (2013.01) [F02C 9/32 (2013.01); F05D 2220/323 (2013.01); F05D 2220/76 (2013.01); F05D 2270/052 (2013.01); F05D 2270/053 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An electricity generation system, comprising:
an engine having a compressor including a rotating shaft;
an electric generator that is connected to the rotating shaft and generates electricity with rotational force of the rotating shaft;
a detector that detects shaft torque of the electric generator;
a short-circuit that short-circuits between terminals of a polyphase electromagnetic coil in the electric generator; and
a control unit configured to control an operational status of the engine or the electric generator on a basis of the shaft torque,
wherein the control unit is configured to control the short-circuit to short-circuit between terminals of the electromagnetic coil in respective phases in a case where the control unit determines that a decrease in the shaft torque is equal to or larger than a predetermined value thereby controlling the electric generator to generate electromagnetic braking torque.