Thermal Buckling and Modal Analysis for Grid Frame Wing Structure of High-speed Flight Vehicles
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摘要: 翼片结构在高速飞行过程中会承受比较大的气动力和气动热形成的复合载荷。为研究网格翼结构的工作热屈曲和热模态特性，进行了理论分析和有限元计算；得到了结构的热屈曲临界温度、均匀及非均匀温度载荷下的热模态参数；发现网格翼结构的热屈曲临界温度要高于相同外形和材料的实体平板翼结构，且高温下结构材料热物理参数对热模态的影响要大于材料弹性参数，非均匀温度载荷下的网格翼结构热模态固有频率数值与均匀温度载荷下有一定区别。Abstract: Wing structure bore harsh composite aerodynamic force and heat environment in high-speed flight. Theoretical analysis and finite element calculation were carried out in order to study the thermal buckling and modal characteristics for grid frame wing structure. The critical temperature of thermal buckling and thermal modal parameters under homogeneous or inhomogeneous temperature for the model was obtained. It demonstrated the critical temperature of thermal buckling for grid frame wing structure is higher than plate wing structure's, the thermal physics parameters of material had more prominent effect on thermal modal than elastic parameters under high temperature, and the natural frequencies of grid frame wing structure under inhomogeneous temperature was different from under homogeneous temperature.
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Key words:
- wings /
- thermal buckling /
- modal analysis /
- hypersonic vehicles
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表 1 30CrMnSiA材料热物理参数
T/℃ λ/(W·m-1·℃-1) c/(J·kg-1·℃-1) α/(10-5℃-1) E/GPa 20 27.63 473.1 0 196 100 29.30 519.1 1.100 188 200 30.56 581.9 1.172 177 300 30.56 644.7 1.292 167 400 30.56 699.1 1.362 162 500 29.51 766.1 1.390 157 600 28.67 841.5 1.422 152 700 27.21 916.6 1.453 147 800 25.33 991.7 1.343 142 
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表 3 不同温度下网格翼前6阶固有频率
T/
℃1阶/
Hz2阶/
Hz3阶/
Hz4阶/
Hz5阶/
Hz6阶/
Hz20 191 296 527 875 1000 1160 100 186 280 495 831 977 1127 200 177 257 453 769 947 1083 300 168 228 401 697 917 1034 400 157 197 348 629 896 982 500 138 156 288 553 870 912 600 59 81 223 468 814 874 612 0 62 215 457 803 872
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