FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises body with thrust cutoff assemblies furnished with pyrotechnical appliances and joint assembly arranged around said cutoff assemblies. Joint assembly, opposite the thrust cutoff assemblies, have access doors with flanging and covers. Access door flanging represents hollow cylinders arranged aligned with thrust cutoff assemblies. Gaps between flanging and thrust cutoff assemblies exceed travel of said assemblies at maximum strain of the body caused by maximum in-chamber pressure. Flanging has thrust elements in contact with access door covers representing barrels with their skewed bottoms arranged flush with joint assembly outer surface. Outer cylindrical surface of every cover has sealing assembly.
EFFECT: simplified design, higher reliability.
| Title | Year | Author | Number |
|---|---|---|---|
| SOLID PROPELLANT ROCKET ENGINE | 2009 |
|
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RU2109159C1 |
