{
  "$type": "site.standard.document",
  "description": "The present invention relates to a liquid rocket engine impact load structural response prediction method. The present invention aims to provide the liquid rocket engine impact load structural response prediction method in order to solve the technical problems that in the prior art, adopted input…",
  "path": "/patents/1396581",
  "publishedAt": "2026-01-28T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K9/42",
    "XIAN AEROSPACE PROPULSION INSTITUTE [CN]"
  ],
  "textContent": "The present invention relates to a liquid rocket engine impact load structural response prediction method. The present invention aims to provide the liquid rocket engine impact load structural response prediction method in order to solve the technical problems that in the prior art, adopted input loads are all single acceleration loads, and a multi-source load excitation condition in a complex hot test run process is difficult to meet. The present invention integrates a liquid rocket engine complete-machine structural dynamics modeling technology and a multi-excitation-source impact dynamics analysis method, on the basis of reasonably simplifying a liquid rocket engine complete-machine model, forced displacement loads are applied to a plurality of positions to serve excitation inputs, liquid rocket engine complete-machine structural dynamics analysis is developed, structural strength of key parts of an engine and rocking angles of rocking bearings are analyzed, effective evaluation can be provided for engine structural optimization and limit bearing capacity, and then effective prediction is provided for structural strength of the engine in later high-working-condition test run.",
  "title": "METHOD FOR PREDICTING STRUCTURAL RESPONSE OF LIQUID-PROPELLANT ROCKET ENGINE TO IMPACT LOAD"
}