{
  "$type": "site.standard.document",
  "description": "A hybrid electric propulsion (HEP) system included in an aircraft includes a generator (103) configured to output a first power, an energy storage system (102) including a battery (124) configured to output a second power, a propulsion system (205) configured to generate thrust based on at least…",
  "path": "/patents/1388973",
  "publishedAt": "2025-12-17T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "B60L15/20",
    "RTX CORP [US]"
  ],
  "textContent": "A hybrid electric propulsion (HEP) system included in an aircraft includes a generator (103) configured to output a first power, an energy storage system (102) including a battery (124) configured to output a second power, a propulsion system (205) configured to generate thrust based on at least one of the first power and the second power, and an HEP controller (200) in signal communication with the generator (103), the energy storage system (102), and the propulsion system (205). The HEP controller (200) is configured to detect loss of the first power output from the generator (103), to determine an altitude of the aircraft and to actively control delivery of the second power to the propulsion system (205) based on the altitude during the loss of the first power.",
  "title": "AIRCRAFT HYBRID ELECTRIC PROPULSION ARCHITECTURE WITH GENERATOR-MOTOR FAIL MODE"
}