Investigation Of The Burning Rate Model Of Nano-aluminum Ice Solid Propellants

Nano-scale aluminum powder is used as the rocket propellant,which is a new way to develop the green space propulsion system.It is combustion form can be aluminum-water or aluminum-ice(ALICE).The ALICE which possesses characteristics of simple structure,high reliability and impulse,has potential application background.The main work of this thesis is to discuss combustion rate and characterization of ALICE,and analysis the effect of different parameters on the burning rate of ALICE.Main contents are as follows:Firstly,the combustion and characterization of ALICE has been observed through the combustion experiment.While the experimental data being sorted and analyzed,the results show that,the burning rate increases with rising the initial temperature.The effect of the initial temperature on the burning rate decreases with increasing pressure when the water-fuel ratio was less than 1,while increases with increasing pressure when the water-fuel ratio was greater than 1,When the water-fuel ratio was 1,a maximum burning rate could be got.Secondly,the granular diffusion flame model was used to study the burning rate and characterization of ALICE,and the effect of different parameters on the burning rate pressure curves was studied.The results show that,changing the pre-exponential factor of the Arrhenius formula and aluminum particle size will result in a substantial change in the burning rate pressure exponent.There is little effect on the pressure exponent while the other factors(including the density,specific heat,the surface temperature of propellant,flame temperature,thermal conductivity,the passivation of the nano-aluminum powder,the water-fuel ratio and the initial temperature)changed.And these factors will change the burning rate.Finally,a burning rate model has been built on the basis of the Vigor Yang's Al-H2O combustion model to study the temperature structure of the combustion process of ALICE and to have a full understanding on the combustion characterization of ALICE.The exact solution and approximate solution that are two ways to calculate the burning rate have been proposed.The result which was calculated by the two methods is closer to the experimental result.Through analyzing the various regions of flame structure found that the thickness of each region reduces and the heating rate increases with increasing pressure.By studying the effect of these factors(including the passivation of the nano-aluminum powder,the initial temperature,the water-fuel ratio and aluminum particle size)on the burning rate of ALICE solid propellant,found that the burning rate increases with increasing the initial temperature,but decreases with increasing these factors that including the passivation of the nano-aluminum powder,the water-fuel ratio and aluminum particle size;the thickness of each region decreases with increasing the passivation of the nano-aluminum powder and the water-fuel ratio,but increases with increasing aluminum particle size;the thickness of Al-water zone and reaction zone increase with increasing the initial temperature,while the thickness of Al-water vapor zone decrease with increasing the initial temperature.