{
  "$type": "site.standard.document",
  "description": "An aircraft assembly includes an engine core (48), a first electrical power system (34A) and a second electrical power system (34B). The first electrical power system (34A) includes a first electric machine (96A) and a first electric machine controller (98A). The first electric machine (96A) is…",
  "path": "/patents/1427156",
  "publishedAt": "2026-06-24T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B64D27/10",
    "RTX CORP [US]"
  ],
  "textContent": "An aircraft assembly includes an engine core (48), a first electrical power system (34A) and a second electrical power system (34B). The first electrical power system (34A) includes a first electric machine (96A) and a first electric machine controller (98A). The first electric machine (96A) is operatively coupled to the engine core (48). The first electric machine controller (98A) is electrically coupled to the first electric machine (96A). The first electric machine controller (98A) is configured to control operation of the first electric machine (96A). The second electrical power system (34B) is electrically discrete from the first electrical power system (34A). The second electrical power system (34B) includes a second electric machine (96B) and a second electric machine controller (98B). The second electric machine (96B) is operatively coupled to the engine core (48). The second electric machine controller (98B) is electrically coupled to the second electric machine (96B). The second electric machine controller (98B) is configured to control operation of the second electric machine (96B).",
  "title": "AIRCRAFT ELECTRICAL POWER SYSTEM(S) WITH ELECTRIC MACHINE(S)"
}