سال انتشار: ۱۳۸۶

محل انتشار: پنجمین کنگره بین المللی مهندسی شیمی

تعداد صفحات: ۱۰

نویسنده(ها):

Ahmad Reza Bahramian – Polymer Engineering Group, Tarbiat Modares University (TMU), Tehran, I. R. Iran.
Mehrdad Kokabi – Polymer Engineering Group, Tarbiat Modares University (TMU), Tehran, I. R. Iran.
Mohammad Hossein Navid Famili – Polymer Engineering Group, Tarbiat Modares University (TMU), Tehran, I. R. Iran.
Mohammad Hossein Beheshty – Iran Polymer and Petrochemical Institute, Tehran, I. R. Iran.

چکیده:

Spacecraft heat shield use thermal protection system materials which ablate at high temperature for mass efficient rejection of aerothermal heat load. Recent advances in polymer layered silicate nanocomposites especially improved heat protection performance. Additionally, provided that the char remains intact, resistance to thermal and chemical ablation ultimately limits lifetime. Mass and energy balance equations have been solved in order to model the ablation of an ablative material. A method to determine and calculate some of the parameters in the ablative equation is proposed from the simultaneous thermal gravity and differential scanning calorimetry analysis techniques. Inverse analysis techniques have been used successfully for the estimation of thermal properties of ablating materials. The objective of this work is to model ablating and thermal degradation behaviour of a heat shield resol-type phenolic resin/asbestos cloth composite and its kaolinite layered silicate nanocomposite in oxyacetylene flame test according to ASTM-E-285-80. All of the theoretical results confirmed with experimental data.