Kinetic laws and calorimetric properties of epoxy composite rocket propellants modified by nanoparticles

摘要

The composite rocket propellants are highly filled composite materials. The typical composition of composite solid rocket propellant is based on crystalline solid oxidizer bound together with polymeric matrix. Many other additives like metal particles, nitramine crystals, ballistic modifiers, may be included in the final mixture depending on the desired use of the propellant. The aim of the work is to study the effect of adding nanoclays such as montmorillonite type one, on the kinetic and calorimetric properties of a rocket composite propellant based ammonium perchlorate as oxidiser and epoxy/amine binder system. The first part of the study deals with the preparation of rocket propellant specimens adapted for Crawford's and adiabatic calorimeter tests, loaded with different types of nanoclays. We have to determine some experimental conditions in order to satisfy the qualities required by the combustion phenomenon and especially the homogeneity of the block. The second part consists in one hand on the characterization of propellant systems by Crawford apparatus for determination of burning rate versus pression to establish combustion laws and adiabatic calorimeter for the calorimetric investigation.