{
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  "description": "A hybrid-electric aircraft system (401) includes first and second hybrid-electric engines (410, 420), first and second ducting systems (430, 440) fluidly communicative with each other and with the first and second hybrid-electric engines (410, 420), respectively, and a control system. The control…",
  "path": "/patents/1400269",
  "publishedAt": "2024-08-28T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D13/06",
    "RTX CORP [US]"
  ],
  "textContent": "A hybrid-electric aircraft system (401) includes first and second hybrid-electric engines (410, 420), first and second ducting systems (430, 440) fluidly communicative with each other and with the first and second hybrid-electric engines (410, 420), respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines (410, 420) and to each of the first and second ducting systems (430, 440). The control system is configured to run the first hybrid-electric engine (410) normally, to run the second hybrid-electric engine (420) in a lower power mode and to control each of the first and second ducting systems (430, 440) to direct bleed air from the first hybrid-electric engine (410) to the second hybrid-electric engine (420).",
  "title": "HYBRID-ELECTRIC SINGLE ENGINE DESCENT ENGINE MANAGEMENT"
}