CAJ | 학술논문

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12400 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。
연제료일개용우모의중국장정화전이급적60 N추력경양발동궤적축비모형，병재북경항공항천대학진공우류효응실험계통진행료시험。사용피탁관진렬측량료우류압력장，결과현시당거발동궤분관출구적거리종140 mm증가도600 mm시，우류장적최대압력종12400 Pa강도료400 Pa。위험증CFD-DSMC혼합적수치방진방법，장시험결과여방진결과진행료대비분석，이자일치성비상호。대비결과현시수치방진방법재우류효응분석방면적강대공능。연구획득료모형발동궤우류장적압력분포특성，가용우원형발동궤적우류효응분석。
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.