{
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  "description": "A control system (34) for an aircraft hybrid propulsion system (5). The hybrid propulsion system (5) comprises a gas turbine engine (10) coupled to an electric generator (28, 32), a propulsor (12) coupled to an electric motor (28), and an electrical storage device (30) coupled to the motor (28) and…",
  "path": "/patents/1413132",
  "publishedAt": "2023-05-31T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D27/02",
    "ROLLS ROYCE PLC [GB]"
  ],
  "textContent": "A control system (34) for an aircraft hybrid propulsion system (5). The hybrid propulsion system (5) comprises a gas turbine engine (10) coupled to an electric generator (28, 32), a propulsor (12) coupled to an electric motor (28), and an electrical storage device (30) coupled to the motor (28) and the generator (32). The control system (34) is configured to operate the propulsion system (5) in one of a first descent mode and a second descent mode. In the first descent mode, for a given thrust, the gas turbine engine (10) is operated at a first engine power level and the generator (28, 32) is operated at a first generator power level. In the second descent mode, for a given thrust, the gas turbine engine (10) is operated at a second engine power level which is higher than the first engine power level, and the generator (28, 32) is operated at a second generator power level which is higher than the first generator power level. Electric power generated by the electric generator (28, 32) during operation in the second descent mode is stored in the electrical storage device (30).",
  "title": "AIRCRAFT PARALLEL HYBRID PROPULSION SYSTEM"
}