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Information Journal Paper

Title

MODELLING THE DEGRADATION PROCESS OF ABLATIVE COMPOSITES

Pages

  313-318

Abstract

 If the bodies, such as the head and nose of missile, nozzle or combustion chamber of the rocket, which are exposed to sever heat, are not protected against it, then they cannot perform for the purpose they are designed. One of the recommended methods to protect these systems against heat is the usage of the ablative insulators. In this work, the thermal behavior of ABLATIVE COMPOSITEs of SILICON RUBBER matrix and glass reinforced fibers was studied and modelled. For this purpose, the mass and energy equation in ablation conditions were simultaneously solved numerically using finite difference method and the various related parameters of the insulator were determined as a function of temperature and time. This modelling will allow to predict the proper thickness of the ABLATIVE COMPOSITE in the actual service conditions. This method can also be used in designing of the other ABLATIVE COMPOSITEs.

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    APA: Copy

    BAHRAMIAN, A.R., & KOKABI, MEHRDAD. (2004). MODELLING THE DEGRADATION PROCESS OF ABLATIVE COMPOSITES. IRANIAN JOURNAL OF POLYMER SCIENCE AND TECHNOLOGY (PERSIAN), 16(5 (ISSUE NO. 67)), 313-318. SID. https://sid.ir/paper/6169/en

    Vancouver: Copy

    BAHRAMIAN A.R., KOKABI MEHRDAD. MODELLING THE DEGRADATION PROCESS OF ABLATIVE COMPOSITES. IRANIAN JOURNAL OF POLYMER SCIENCE AND TECHNOLOGY (PERSIAN)[Internet]. 2004;16(5 (ISSUE NO. 67)):313-318. Available from: https://sid.ir/paper/6169/en

    IEEE: Copy

    A.R. BAHRAMIAN, and MEHRDAD KOKABI, “MODELLING THE DEGRADATION PROCESS OF ABLATIVE COMPOSITES,” IRANIAN JOURNAL OF POLYMER SCIENCE AND TECHNOLOGY (PERSIAN), vol. 16, no. 5 (ISSUE NO. 67), pp. 313–318, 2004, [Online]. Available: https://sid.ir/paper/6169/en

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