摘要
叙述了羽流效应地面模拟试验系统由高空模拟试车台向真空试验系统发展的过程,指出引射原理的局限性和低温冷凝技术的适用性.介绍了应用低温冷凝技术建成的美国CHAFF-4(the collaborative high altitude flow facility-Ⅳ)系统和德国STG(Simulationsanlage für Treibstrahlenin Gttingen)系统及中国首座大型羽流效应地面模拟试验系统——PES(the plume effects experimental system)系统.采用直接模拟蒙特卡罗DSMC(direct simulation Monte Carlo)方法对PES设备的内置式液氦深冷泵的抽气能力进行了数值模拟研究,结果表明无论有无羽流吸附泵时,2g/s级发动机点火时,内置式液氦深冷泵都能满足发动机出口截面后φ4m×5m范围内的背压小于10-3 Pa,羽流吸附泵能有效地阻止压缩波向喷管方向推进.
The development process of vacuum plume effects ground simulation test facilities from high altitude simulation test facilities to vacuum test system was described.The limitation of ejector principle and the applicability of cryogenic condensation technology were described.The American CHAFF-4（the collaborative high altitude flow facility-Ⅳ） facility,German STG（Simulationsanlage für Treibstrahlenin Gttingen） facility and China＇s first large-scale vacuum plume effects ground simulation experimental system—PES（the plume effects experimental system）facility were introduced,all of which were constructed based on the low temperature condensation technology.Details of the initial simulation investigation of PES＇s built-in LHe cryogenic pumping were presented along with the results from a direct simulation of Monte Carlo（DSMC）.The results demonstrate that,with or without the plume cryogenic pumping,at 2g/s stage thruster working condition,the built-in liquid helium cryogenic pumping can meet the condition that the environment of the back pressure,in the region of 4m×5m,is less than 10-3Pa,and plume cryogenic pumping can effectively prevent the compression wave from diffusion to the nozzle direction.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第4期900-906,共7页
Journal of Aerospace Power
基金
中俄航天合作项目
关键词
真空羽流
地面模拟试验系统
低温冷凝技术
深冷泵
高空模拟
vacuum plume
ground simulation experimental system
low temperature condensation technology
cryogenic pumping
high altitude simulation
