高温复合材料与高超声速气流相互作用研究
文献类型：学位论文
| 作者 | 蔺晓轩 |
| 学位类别 | 硕士 |
| 答辩日期 | 2010-05-19 |
| 授予单位 | 中国科学院研究生院 |
| 导师 | 张伟刚 |
| 关键词 | 高温复合材料 高超声速 气动热 热应力 高温隔热性能 |
| 其他题名 | Study on the phenomena of high temperature composite materials in hypersonic flows |
| 学位专业 | 化学工程 |
| 中文摘要 | 高超声速飞行器在大气层里飞行过程中与周围空气发生强烈相互作用而受到严重气动加热，准确地进行气动加热计算和热防护设计一直是研制高超声速飞行器的技术关键。 针对前缘构件的超高温材料，分别采用有限差分法和有限单元法对超燃冲压发动机用ZrB2-SiC前缘构件高超声速气动加热过程及其内部热应力进行了数值模拟，并以电弧风洞地面模拟实验对计算结果进行了验证。计算结果表明，当飞行马赫数为6，总温2375 K，总压4.41 MPa，结构前缘半径0.125 mm时，驻点温度5 s达到1870 K，内部最大热应力达到1240 MPa，这将导致服役过程中材料的失效。电弧风洞实验表明，驻点温度5 s达到2175 K，材料前缘因承受的应力超过其弯曲强度而断裂。计算结果与风洞实验结果吻合较好。 针对大面积热防护材料，本文设计了一套隔热材料高温(>1200 ℃)隔热效果的测试装置，可在前期代替高超声速风洞实验，可对隔热材料进行快速、 低成本的有效测试和筛选。采用本装置在材料冷壁热流值为4.13×105 W/m2，材料热面中心温度为1600±10 ℃时，考察了炭/酚醛材料、ZrO2纤维板材料和两种新型耐高温复合多层隔热材料的背部升温历程，评价其隔热性能，并采用有限差分法数值模拟了ZrO2纤维板材料背部升温历程，预测其有效导热系数。研究表明，在加热初期400 s时间内，炭/酚醛复合材料的隔热性能优于ZrO2纤维板的隔热性能，后期则相反；ZrO2纤维板的隔热性能与其体积密度有关，其有效导热系数随温度升高而非线性地增大。设计的新型耐高温复合多层隔热材料总厚度35.4 mm，经过700 s隔热测试后冷面中心背温为20 ℃，将成为航空航天隔热候选材料。 |
| 英文摘要 | Hypersonic vehicles will suffer both serious aerodynamic force and aerodynamic heating during flighting and interacting with the environment air. Therefore, calculation and simulation of aerodynamic heating and thermal protection design on the surface of the vehicles become the key technology. In accordance with the leading edge components at the ultra high temperature zone, aerodynamic heating process and thermal stress of ZrB2-SiC leading edge as the component of scramjet engines were numerically investigated by finite-difference and finite-element methods. Simulation results were verified through thermal structure tests with arc-heated wind tunnels. Simulation results show that temperature at stagnation point reaches 1870 K in 5 s，and thermal stress of structure is up to 1240 MPa which is beyond the fracture strength of ZrB2-SiC material, when the inflow mach number is 6, total pressure is 4.41 MPa, total temperature is 2375 K, radius of the leading edge is 0.125 mm. The experimental results show that temperature at stagnation point reached 2175 K in 5 s, and the leading edge cracked in thermal structure tests. Simulation results are in reasonable agreement with the experimental results. In accordance with large area thermal insulation materials, a device for thermal insulation performance of high-temperature materials was designed and established to test light weight thermal-insulation materials via a rapid and simple procedure. Thermal insulation performance of carbon fiber/phenolic material, ZrO2 fiberboard and two kinds of new-typed high temperature endurable multilayer insulation materials was tested by this device when the cold-wall heat flux was 4.13×105 W/m2, and temperature at the center point of hot face was 1600±10 ℃. The heat transport process of ZrO2 fiberboard was numerically simulated by finite-difference method, and the effective thermal conductivity was also predicted. The results show that thermal insulation performance of carbon fiber/phenolic material is better than that of ZrO2 fiberboard from the beginning of test to 400 s, while the thermal insulation performance of ZrO2 fiberboard is better from 400 s to the end of test. Thermal insulation performance of ZrO2 fiberboard is affected by the bulk density, and the effective thermal conductivity of ZrO2 fiberboard increases nonlinearly with the elevated temperature. The thickness of the new-typed high-temperature endurable multilayer insulation was 35.4 mm, the back temperature at the centre zone was 20 ℃ after 700 s heating test, and it will be the candidate material in the fields of aeronautical and astronautical technologies. |
| 语种 | 中文 |
| 公开日期 | 2013-09-22 |
| 页码 | 77 |
| 源URL | [http://ir.ipe.ac.cn/handle/122111/1636]  |
| 专题 | 过程工程研究所_研究所（批量导入） |
| 推荐引用方式 GB/T 7714 | 蔺晓轩. 高温复合材料与高超声速气流相互作用研究[D]. 中国科学院研究生院. 2010. |
入库方式： OAI收割
来源：过程工程研究所
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