HAN基单组元发动机均匀分配喷注器设计及试验研究（“液体火箭推进”专刊）

硝酸羟胺基（简称HAN）推进剂要比肼类推进剂稳定，将相同质量的HAN基推进剂完全分解，HAN基推进剂所需的时间要比肼推进剂要长。为了增大推进剂与催化剂的初始接触面积，使推进剂在催化床内均匀分布，开展了发动机喷注器的均匀分配方式研究。通过采用VOF模型对新型喷注器结构的喷注过程和雾化效果进行数值仿真研究，为喷注器结构优化提供理论支持。同时通过三维PDA（Phase Doppler Anemometry）测量系统，获得了两种喷注器结构雾化液滴空间上的密度分布、直径大小以及轴向速度等对比情况。最后，通过地面热试车试验，对两种喷注器结构的发动机在脉冲温启动、稳态工作性能及燃烧反应特性等方面进行了对比，带喷注芯体的喷注器结构在开机响应特性和燃烧性能方面都更好。

Design and Experimental investigation on a HAN-based Monopropellant Thruster with uniform distributed injector

Compared to hydrazine, Hydroxyl ammonium Nitrate (HAN) is more stable and takes longer to be completely decomposed. In order to improve the initial contact area between the propellant and the catalyst to make the propellant evenly distributed in the catalytic bed, the uniform distributed method of the injector is studied. The numerical simulation research on the injection process and atomization effect of the new injector structure has been carried out by using the Volume of Fluid (VOF) model, it provided theoretical support for the optimization of the injector structure. At the same time, the comparison of the density distribution, diameter and axial velocity of the atomized droplet in space of the two injector structures are detected by the three-dimensional phase Doppler Anemometry (PDA). Finally, through the hot fire test on the ground, the performance of the thruster with two types of injector structure under warm start pulse test, steady-state test and combustion reactivities have been compared, and it has concluded that the structure with injection core is better under starting response characteristics and combustion performance.