摘要
研制了一个用于模拟中国长征火箭二级的60 N推力氢氧发动机的缩比模型,并在北京航空航天大学真空羽流效应实验系统进行了试验。使用皮托管阵列测量了羽流压力场,结果显示当距发动机喷管出口的距离从140 mm增加到600 mm时,羽流场的最大压力从12 400 Pa降到了400 Pa。为验证CFD-DSMC混合的数值仿真方法,将试验结果与仿真结果进行了对比分析,二者一致性非常好。对比结果显示数值仿真方法在羽流效应分析方面的强大功能。研究获得了模型发动机羽流场的压力分布特性,可用于原型发动机的羽流效应分析。
A scaled model thruster of hydrogen/oxygen with a thrust of 60 N, to simulate the second stage engine of the Chinese ‘CZ’ launch vehicle, is designed and tested in the Plume Effect Experimental System （PES） at Beihang University. The pressure field of the plume is determined by using a pitot tube array, and it is shown that the maximum pressure in the plume field decreases from 12400 Pa to 400 Pa while the axial distance away from the nozzle exit increases from 140 mm to 600 mm. The experimental results are compared with the numerical solutions to validate the numerical method integrating both CFD and DSMC, and excellent agreement is shown. The results demonstrate the powerful ability of the numerical approach to estimate the effects of the plume. The characteristics of the pressure field of the model thruster plume are obtained and can be used in the plume effect analysis of the archetype engine.
出处
《航天器环境工程》
2015年第2期157-161,共5页
Spacecraft Environment Engineering
基金
国家自然科学基金项目"直接求解多组分Boltzmann模型方程的高阶有限元方法及应用"(编号:11302017)
