| 气动热环境下多翼导弹温度场数值模拟 |
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| 引用本文： | 杨志斌,蒋军亮.气动热环境下多翼导弹温度场数值模拟[J].航空计算技术,2014(1):48-51. |
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| 作者姓名： | 杨志斌 蒋军亮 |
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| 作者单位： | 中国飞机强度研究所全尺寸飞机结构静力、疲劳航空科技重点实验室,陕西西安710065 |
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| 基金项目： | 航空支撑项目资助（61901030203） |
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| 摘 要： | 导弹在飞行过程中与大气摩擦产生的热量,会降低材料的强度极限和飞行器结构的承载能力,使结构产生热变形,破坏部件的气动外形并影响飞行器的安全飞行,带来安全隐患。通过气动加热工程算法确定表面热流密度,利用有限元分析软件MSC Nastran和MSC Patran,对四翼导弹进行有限元计算,给出温度场分布情况,为导弹的设计和制造提供依据。
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| 关 键 词： | 飞行器 超音速 气动加热 传热 |
Temperature Field Numerical Simulation of Multi- wing Missiles of Aeroheating |
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| Institution: | YANG Zhi- bin, JIANG Jun- liang (Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue, Aircraft Strength Research Institute of China ,Xi＇an 710065, China) |
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| Abstract: | When the aircraft flies at high speed in the air, ultimate stress of material and bearing capacity of aircraft structure are reduced by aerodynamic heating. Moreover, aerodynamic heating makes aircraft structure generate thermal deformation which destroys aerodynamic configuration of aircraft and affects the safety of aircraft flight. In this paper, heating rates on the surface of aircraft were calculated with engineer- ing method by author. Ultimately, the temperature field on the surface of four- winged missile was calcu- lated and analyzed with the finite element analysis software MSC Nastrart/Patran to provide the foundation of missile＇s design and manufacture. |
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| Keywords: | flight vehicle supersonic flow aeroheating heat transfer |
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