{
  "$type": "site.standard.document",
  "coverImage": {
    "$type": "blob",
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  "description": "The rocket motor combustion chamber (1) is constituted by a first monolithic thermo-structural composite material comprising a porous skin (5) through which a part of the fuel is introduced into the heart (C) of the combustion chamber. The combustion chamber is connected by a neck (3) to a…",
  "path": "/patents/1093421",
  "publishedAt": "2003-09-10T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K9/52",
    "EADS LAUNCH VEHICLES [FR]"
  ],
  "textContent": "The rocket motor combustion chamber (1) is constituted by a first monolithic thermo-structural composite material comprising a porous skin (5) through which a part of the fuel is introduced into the heart (C) of the combustion chamber. The combustion chamber is connected by a neck (3) to a divergent pipe (2) through which the exhaust gases pass.",
  "title": "Rocket motor"
}