大尺寸结构部件电弧风洞烧蚀试验技术  

Ablation test technique of large scale structure component in arc-heated wind tunnel

作　　者：欧东斌[1] 陈连忠[1] 董永晖[1] 彭锦龙[1] 陈峰[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2015年第5期661-666,共6页Acta Aerodynamica Sinica

摘　　要：在现有试验设备能力的基础上，结合超声速导管和冷气包罩试验技术，利用水冷挡板和气冷石英玻璃窗口组合形成包围气流通道，解决喷管出口气流继续膨胀导致流场参数衰减严重的问题，对大尺度翼结构部件进行了流场标定，显示翼面热流衰减量由51．5％～73．6％减少为34．0％～40％，翼前缘最大热流衰减量由68．0％减少为43．7％，模型表面热流分布均匀性有明显提高；同时，相对于壁面完全封闭的导管／包罩试验，透过气冷石英玻璃窗口还可以观察大尺寸结构部件实时烧蚀过程并且测量部件表面温度。研究表明该试验技术能够有效用于大尺寸部件防隔热及热结构性能考核研究。It is a great challenge for arc heater facilities to carry out large scale thermal struc-ture test,because this kind of test need high power arc heater and large scale supersonic nozzle. Based on the capability of existing arc heater facility,the flow field of large scale wing compo-nents is calibrated using improved supersonic turbulent duct and cold air shrouded flow tech-nique.In the test,by means of the air channel constituted with water cooling copper panels and gas cooling quartz glass,the serious problem of flow field attenuation caused by the flow expan-sion at the nozzle outlet is solved successfully.The calibration result shows that the heat flux de-creases on the wing surface and wing edge have changed from 51.5%~73.6% to 34.0%~40.0%and 68.0% to 43.7% respectively,and the heat flux distribution on the wing becomes more uni-form.At the same time,there is a significant difference from the traditional closed supersonic duct test,the ablation process can be recorded and the surface temperature of the wing can be measured during the test through the gas cooling quartz glass.The test result shows that the techniques mentioned above can be effectively used to evaluate thermal structural performance and survivability of large scale components in arc heated wind tunnel.

关 键 词：大尺寸 电弧风洞 烧蚀 热结构 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]