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- W2365608300 abstract "With the development of the solid rocket technology, the single chamber,dual thrust solid rocket motor is often used in tactical missiles. To confirm the safety of the rocket motor,it is necessary to make a deep research on the heat transfer of the combustion chamber and the nozzle. An analysis system is presented in this paper,which includes computation of grain geometric shape,internal flow field,heat transfer and ablation. And a set of ripe software has been developed. An example of designing the safety thickness of the insulation structure and ablator is given. By comparig the calculation result with the practically thickness, the system is proved credible and convenient." @default.
- W2365608300 created "2016-06-24" @default.
- W2365608300 creator A5034668583 @default.
- W2365608300 date "2002-01-01" @default.
- W2365608300 modified "2023-09-24" @default.
- W2365608300 title "Safety limits design system of heat protection for combustion chamber and nozzle of solid rocket motor" @default.
- W2365608300 hasPublicationYear "2002" @default.
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