FIELD: engines and pumps.
SUBSTANCE: integral rocket ramjet engine consists of gas generator with a hard fuel charge, combustion chamber equipped with at least one branch, non-removable cover, arranged on the branch; the said cover has a case with a grid composed of longitudinal and transverse ribs, and a plate of a laminated structure. The grid is of full strength with a wall of the combustion chamber and projects into the combustion chamber at a thickness of a heat shielding coating of the latter. The plate consists of metal foil and protecting adhering layer. A heat shielding coating is applied on an inside surface of the combustion chamber; while a protecting adhering layer is applied on the surface of the said coating.
EFFECT: increased reliability of an integral rocket ramjet engine at the transitive stage from a start to cruise mode; upgraded conditions of air flow supply into a combustion chamber and increased ratio of recovery of a combustion chamber full pressure during engine operation.
3 cl, 9 dwg
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