Heat insulation material for combustion chamber of solid rocket engine
The invention discloses a thermal insulation material for a combustion chamber of a solid rocket engine, which comprises a low-density layer attached to the inner wall of the combustion chamber of the solid rocket engine and an ablation-resistant layer positioned on the outer side of the low-density...
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Format: | Patent |
Sprache: | chi ; eng |
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Zusammenfassung: | The invention discloses a thermal insulation material for a combustion chamber of a solid rocket engine, which comprises a low-density layer attached to the inner wall of the combustion chamber of the solid rocket engine and an ablation-resistant layer positioned on the outer side of the low-density layer and vulcanized together with the low-density layer, and the thickness ratio of the low-density layer to the ablation-resistant layer is 3: 1; the density of the heat insulation material is 0.7071 to 0.7123 g/cm < 3 >; the linear ablation rate ranges from 0.03573 mm/s to 0.05640 mm/s; the carbonization ablation rate ranges from 0.1712 mm/s to 0.1834 mm/s; a foam structure is introduced into the EPDM thermal insulation material through a rubber foaming technology, so that the density of the thermal insulation material can be remarkably reduced; and then the ablation-resistant layer and the low-density layer are combined through vulcanization, so that the density of the thermal insulation material can be reduce |
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