| Through using a theoretical combustion model of quasi-one dimensional steadyreactive gas-phase for solid propellants, the mechanism and model of composite solidpropellants are investigated, whose content is as followings:(1) Through exploring laws of thermal decomposition of the high-energycomponents including AP,HMX,RDX, their decomposition mechanism and production atinitial combustion stage are established. A model for calculating the burning rate ofhomogenous propellants of high-energy explosives is developed and proved. At the sametime, optimal catalysis effect can be predicted on buming performance of high-energycomponents.(2) On the basis of composite solid propellants combustion model, we have modifiedthe surface structure factor of nitroamine propellants and a new function have be used tomodified the decomposition products of nitroamine according to predecessors' researchfindings in combustion mechanism of nitroamine propellants, these work make originalmodel is indicated for a wide range of pressure and particle size.(3) A modified factor of gAl is lead into original model according to coherencecombustion mechanism of aluminum powder, make the combustion model ofaluminiferous propellants accord with real combustion process and make the model refersto the propellants which contains fine grain aluminum powder.(4) On the basis of the non-catalyze model for prediction burning rate, the effect ofCNTs,Fe2O3 and Fe2O3/CNTs catalyst on the combustion of composite solid propellantswas studied, a g(P,X) function and catalytic activity parameter C is lead into original model,the catalytic combustion formula of composite solid propellants is established. Using theestablished model, theories calculation values are agree with measure values.(5) Series parameter of some components which were chosen according to theultimate composition of composite solid propellants was calculated for to predict the affectof these components to the combustion of propellants. |
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