Hou Yangyang, Yu Yusong, Liu Xuhui, Cao Jie
Hydrogen Energy and Space Propulsion Laboratory, School of Mechanical, Electronic and Control Engineering, Beijing Jiaotong University, Beijing 100044, China.
Beijing Institute of Control Engineering, Beijing 100190, China.
Micromachines (Basel). 2022 Apr 12;13(4):605. doi: 10.3390/mi13040605.
In this paper, numerical simulations were used to study the decomposition and combustion processes inside the 0.2 N-class ADN-based thruster, and the effects of two geometrical parameters (length and diameter) of the combustion chamber on the combustion performance were evaluated. The decomposition and combustion processes of the thruster were simulated using a reduced chemical reaction mechanism with 22 components and 20 reactions steps. According to the distribution of the basic physical fields, the variation patterns of the pressure field, velocity field, temperature field, and key component parameters caused by different combustion chamber geometrical parameters were observed and analyzed. The results show that the specific impulse and thrust of the thruster increased and then decreased with the increase of the combustion chamber diameter. When the combustion chamber diameter is 7.9 mm, the specific impulse reaches the maximum value of 206.6 s. Additionally, the specific impulse increased from 186 s to 206 s when the combustion chamber length was changed from 7 mm to 11 mm; the specific impulse increased gradually but not significantly, and the growth trend started to flatten out. The results from the paper can serve as a reference for the design and vacuum testing of an ADN-based thruster.
本文采用数值模拟方法研究了0.2 N级基于二硝酰胺铵（ADN）的推进器内部的分解和燃烧过程，并评估了燃烧室的两个几何参数（长度和直径）对燃烧性能的影响。采用包含22种组分和20个反应步骤的简化化学反应机理对推进器的分解和燃烧过程进行了模拟。根据基本物理场的分布，观察并分析了不同燃烧室几何参数引起的压力场、速度场、温度场和关键组分参数的变化规律。结果表明，推进器的比冲和推力随燃烧室直径的增加先增大后减小。当燃烧室直径为7.9 mm时，比冲达到最大值206.6 s。此外，当燃烧室长度从7 mm变为11 mm时，比冲从186 s增加到206 s；比冲逐渐增加但不显著，且增长趋势开始趋于平缓。本文的研究结果可为基于ADN的推进器的设计和真空测试提供参考。
