复合材料壁板颤振分析与优化设计研究
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摘要
随着现代飞行器的性能不断提高，其翼面蒙皮壁板以及金属热防护系统的外面板在高速气流作用下会发生不稳定现象，即壁板颤振。针对此类问题的分析方法，是目前国际上超音速气动弹性研究的热点之一。本文在全面回顾壁板颤振分析方法及其工程应用的基础上，研究了三类复合材料壁板颤振问题及相关优化设计，本文主要工作包括如下几个方面：
(1)提出了偏航壁板颤振速度的概念和分析方法，用以描述现代飞行器做高速机动飞行时，最容易发生壁板颤振的情况。采用模拟退火算法，对不同气流偏角的壁板颤振速度分析，确定最小的壁板颤振速度，即偏航壁板颤振速度。与固定气流偏角下的壁板颤振速度相比，复合材料层合板的偏航壁板颤振速度明显低于其它气流偏角下的颤振速度。当热颤振模态发生变化时，温度场热效应使偏航壁板颤振发生“跳跃”现象，对应的气流偏角发生变化，随温升的增加，壁板热颤振速度先升高后降低，两者呈非线性关系。
(2)利用单目标/多目标模拟退火算法，对复合材料层合板的偏航壁板颤振速度进行了优化设计研究。研究表明：以偏航壁板颤振速度作为目标函数，所获得最优铺层方式能满足所有飞行条件下的机动安全要求，并能有效地解决以不同气流偏角下的壁板颤振速度作为优化设计目标而带来的最优铺层方式选择问题。
(3)提出了一种高效的蜂窝夹层结构简化分析模型，该模型基于三层准三维单元和多孔材料的胞元理论。分析该模型的壁板颤振速度，并验证了其有效性。以该模型的壁板颤振速度为目标函数之一，分别进行了铝合金面板的蜂窝夹层结构的多目标优化设计和复合材料面板的蜂窝夹层结构的多目标优化设计。与初始设计相比，壁板颤振速度得到明显提高，其它目标函数的性能得到改善，并获得了两组优化的Pareto解集。
(4)在Msc.Nastran软件平台上，利用DMAP语言开发了非线性壁板颤振分析程序。通过算例分析，验证了二次开发程序的有效性。建立了具有分层损伤的纤维增强金属层合板(铝合金和玻璃纤维)的有限元模型，综合考虑几何非线性和材料非线性对颤振现象的影响。算例结果表明：分层损伤的出现，将增大复合材料层合板的非线性颤振的振动幅值。当分层面积增大时，壁板颤振出现多种非线性动力学现象(极限环振荡、概周期运动以及多频运动)。当铝合金材料层的应力达到屈服极限时，材料非线性明显增大非线性颤振的振动幅值。
最后对本文工作进行了总结，并展望了未来研究方向。
With the performance of modern vehicles improve continuously, the flutter of skinpanels on the exposed surfaces of supersonic vehicles and outer faceplate of metallicthermal protection system may occur in supersonic flow. Panel flutter analysis currentlyis one of the aeroelastic research hotspots in international community. Based on theoverall review of panel flutter analysis and its application in practical engineering, thisdissertation investigated the problems of flutter analysis and optimization design of threetypes of composite structures. The main research work presented in this dissertationincludes:
(1) An concept for panel flutter speed under yawed flow and analysis method usingthis concept are proposed. With the concept of panel flutter speed under yawed flow，theworst-case flutter analysis can be performed efficiently during maneuvering flight. Thepanel flutter speeds under yawed flow are obtained by means of simulated annealingoptimization algorithm. Compared with panel flutter speed under other flow conditions，panel flutter speed under yawed flow is the minimum speed. On condition that thethermal flutter modes change, the thermal effect could produce transition phenomenon inpanel flutter under yawed flow, and the corresponding flow yaw angle also changes; Theflutter speed first increases and then decreases as the temperature rises which shows anonlinear relationship between flutter speed and temperature elevation.
(2) Single/Multi-objective optimizations are conducted using simulated annealing，the results show that the stacking sequence optimization design could significantlyimprove the panel flutter speed under yawed flow and preferably solve the selectionproblem of the optimal stacking sequence in current panel flutter optimization.
(3) Based on three-layer-quasi-three-dimensional element and cellular theory，ansimplified model for sandwich structure with honeycomb is proposed. An flutter analysisof sandwich structure is performed using simplified model and mumerical resultsdemonstrate the validity of the simplified model. Two groups of multi-objectiveoptimization design are conducted, in which maximum flutter speed for two kinds ofdifferent sandwich structures is taken as one of multi-objective functions. Theoptimization design could significantly improve the panel flutter speed and other objective functions also could obtain a satisfactory effect.Two Paroto Sets wereachieved.
(4) With the software of Msc.Nastran，an analysis program for nonlinear panelflutter is developed using DMAP language and numerical results demonstrate the validityof the programs developed. Considering the effect of geometric nonlinearity andmatieral nonlinearity, a finite element model of fiber reinforced metal laminates(aluminum alloy and fiberglass) with delamination damage is established. Numericalresults show that the present of delamination damage have an important influence on thepanel flutter speed. When the stress reached yield stress, material nonlinearity has animportant effect on limit cycle flutter of fibre reinforced metal laminate and has greaterinfluence limit cycle flutter of fibre reinforced metal laminate with delaminationdamage.
(1)提出了偏航壁板颤振速度的概念和分析方法，用以描述现代飞行器做高速机动飞行时，最容易发生壁板颤振的情况。采用模拟退火算法，对不同气流偏角的壁板颤振速度分析，确定最小的壁板颤振速度，即偏航壁板颤振速度。与固定气流偏角下的壁板颤振速度相比，复合材料层合板的偏航壁板颤振速度明显低于其它气流偏角下的颤振速度。当热颤振模态发生变化时，温度场热效应使偏航壁板颤振发生“跳跃”现象，对应的气流偏角发生变化，随温升的增加，壁板热颤振速度先升高后降低，两者呈非线性关系。
(2)利用单目标/多目标模拟退火算法，对复合材料层合板的偏航壁板颤振速度进行了优化设计研究。研究表明：以偏航壁板颤振速度作为目标函数，所获得最优铺层方式能满足所有飞行条件下的机动安全要求，并能有效地解决以不同气流偏角下的壁板颤振速度作为优化设计目标而带来的最优铺层方式选择问题。
(3)提出了一种高效的蜂窝夹层结构简化分析模型，该模型基于三层准三维单元和多孔材料的胞元理论。分析该模型的壁板颤振速度，并验证了其有效性。以该模型的壁板颤振速度为目标函数之一，分别进行了铝合金面板的蜂窝夹层结构的多目标优化设计和复合材料面板的蜂窝夹层结构的多目标优化设计。与初始设计相比，壁板颤振速度得到明显提高，其它目标函数的性能得到改善，并获得了两组优化的Pareto解集。
(4)在Msc.Nastran软件平台上，利用DMAP语言开发了非线性壁板颤振分析程序。通过算例分析，验证了二次开发程序的有效性。建立了具有分层损伤的纤维增强金属层合板(铝合金和玻璃纤维)的有限元模型，综合考虑几何非线性和材料非线性对颤振现象的影响。算例结果表明：分层损伤的出现，将增大复合材料层合板的非线性颤振的振动幅值。当分层面积增大时，壁板颤振出现多种非线性动力学现象(极限环振荡、概周期运动以及多频运动)。当铝合金材料层的应力达到屈服极限时，材料非线性明显增大非线性颤振的振动幅值。
最后对本文工作进行了总结，并展望了未来研究方向。
With the performance of modern vehicles improve continuously, the flutter of skinpanels on the exposed surfaces of supersonic vehicles and outer faceplate of metallicthermal protection system may occur in supersonic flow. Panel flutter analysis currentlyis one of the aeroelastic research hotspots in international community. Based on theoverall review of panel flutter analysis and its application in practical engineering, thisdissertation investigated the problems of flutter analysis and optimization design of threetypes of composite structures. The main research work presented in this dissertationincludes:
(1) An concept for panel flutter speed under yawed flow and analysis method usingthis concept are proposed. With the concept of panel flutter speed under yawed flow，theworst-case flutter analysis can be performed efficiently during maneuvering flight. Thepanel flutter speeds under yawed flow are obtained by means of simulated annealingoptimization algorithm. Compared with panel flutter speed under other flow conditions，panel flutter speed under yawed flow is the minimum speed. On condition that thethermal flutter modes change, the thermal effect could produce transition phenomenon inpanel flutter under yawed flow, and the corresponding flow yaw angle also changes; Theflutter speed first increases and then decreases as the temperature rises which shows anonlinear relationship between flutter speed and temperature elevation.
(2) Single/Multi-objective optimizations are conducted using simulated annealing，the results show that the stacking sequence optimization design could significantlyimprove the panel flutter speed under yawed flow and preferably solve the selectionproblem of the optimal stacking sequence in current panel flutter optimization.
(3) Based on three-layer-quasi-three-dimensional element and cellular theory，ansimplified model for sandwich structure with honeycomb is proposed. An flutter analysisof sandwich structure is performed using simplified model and mumerical resultsdemonstrate the validity of the simplified model. Two groups of multi-objectiveoptimization design are conducted, in which maximum flutter speed for two kinds ofdifferent sandwich structures is taken as one of multi-objective functions. Theoptimization design could significantly improve the panel flutter speed and other objective functions also could obtain a satisfactory effect.Two Paroto Sets wereachieved.
(4) With the software of Msc.Nastran，an analysis program for nonlinear panelflutter is developed using DMAP language and numerical results demonstrate the validityof the programs developed. Considering the effect of geometric nonlinearity andmatieral nonlinearity, a finite element model of fiber reinforced metal laminates(aluminum alloy and fiberglass) with delamination damage is established. Numericalresults show that the present of delamination damage have an important influence on thepanel flutter speed. When the stress reached yield stress, material nonlinearity has animportant effect on limit cycle flutter of fibre reinforced metal laminate and has greaterinfluence limit cycle flutter of fibre reinforced metal laminate with delaminationdamage.
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