| At present, one of the development priorities of liquid rocket engine is the application of high-energy-density azide propellants. DMAZ, one of new azide propellants, calls attention to scientist due to its characteristics of high-energy-density and non-toxic. Though Its combustion performance is close to methylhydrazine(MMH), its toxicity is much littler than latter.DMAZ/NTO, which is one of bipropellant combinations in DMAZ, is selected as research object for researching its design scheme of the propulsion in this paper. Firstly, the theoretical combustion performance of DMAZ/NTO is calculated with the method of the chemical formula thermodynamic calculation. The difference combustion performances between DMAZ and MMH are analyzed on the basis of the calculation results. It's reported that temperature of combustion chamber and the density specific impulse of the former is slightly larger than the latter. Then the thrust chamber, which including injector, combustion chamber and nozzle, is designed for the bipropellant combination. The design of injector includes diameter of spray nozzle, the distribution of spray nozzle and the form of injector. The design of combustion chamber confirms the parameter of shape, volume and dimmeter of combustion chamber. The design of nozzle includes divergence ratio, contraction section and expansion section. On the basis of thermodynamic calculation and thrust chamber design, calculation model is built with appropriate assumptions and combustion numerical model. Reasonable numerical simulation results are obtained through the model, which is consistent with the actual combustion process. With comparing and analysing the results from the model between DMAZ/NTO and MMH/NTO, It reported that the combustion performance of both is similar. In addition, it's concluded that the increase of length on the combustion chamber can improve the propellant combustion efficiency within a certain range. |
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