{
  "$type": "site.standard.document",
  "description": "The engine (S1) has a circular annular detonation chamber (2) i.e. continuous detonation wave chamber, equipped with an air injection bottom (3) at upstream end and terminated by an ejection nozzle (4) at downstream end. An annular air inlet (5) is connected to the detonation chamber to supply air…",
  "path": "/patents/995855",
  "publishedAt": "2012-11-21T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K7/08",
    "MBDA FRANCE [FR]"
  ],
  "textContent": "The engine (S1) has a circular annular detonation chamber (2) i.e. continuous detonation wave chamber, equipped with an air injection bottom (3) at upstream end and terminated by an ejection nozzle (4) at downstream end. An annular air inlet (5) is connected to the detonation chamber to supply air (F1). A fuel injection unit formed of a supply assembly (6) continuously injects fuel (F2) directly into the detonation chamber immediately downstream of the bottom. The injection of fuel and air into the detonation chamber is performed separately in a permanent manner during operation of the engine.",
  "title": "Ramjet engine with detonation chamber and aircraft comprising such a ramjet engine"
}