基于欧拉—拉格朗日方法的复合材料机翼前缘鸟撞模拟

复合材料大面积用于飞机结构后,其鸟撞问题变得更加突出。利用大型通用有限元程序ABAQUS,采用耦合欧拉—拉格朗日方法（CEL）对某型无人机复合材料机翼前缘的鸟撞问题进行模拟,研究了鸟体速度、密度和蒙皮铺层形式等对鸟撞动响应的影响,计算了机翼前缘填充泡沫后的鸟撞损伤,对复合材料蒙皮的鸟撞破坏机理进行了分析,所得结果对工程设计具有参考意义。     

基于不同构型辅助梁的民机尾翼前缘设计与抗鸟撞性能研究

民用飞机对尾翼前缘的抗鸟撞性能有很高要求。某型民机尾翼前缘原始辅助梁为铝合金机加件,为了优化其抗鸟撞性能,提出了两种使用铝合金钣金辅助梁的尾翼前缘新构型。通过PAM-CRASH软件对三种前缘的抗鸟撞性能进行了数值计算,并根据计算结果在两种新构型中选择了抗鸟撞性能更好的作为优选构型。针对前缘原始构型和和优选构型开展鸟撞试验和试后计算分析。数值计算和试验结果都表明,该研究提出的带"波纹加强筋"的钣金辅助梁结构没有硬点,且材料延展性较好,可以通过结构发生大变形、紧固件大量失效吸收鸟撞过程中的能量,从而大幅提高尾翼前缘的抗鸟撞性能,而且该结构还具有明显的质量优势,可以应用于民机尾翼前缘抗鸟撞设计。     

复合材料加筋壁板鸟撞动响应分析

考虑复合材料蜂窝夹芯结构的冲击损伤,采用接触碰撞耦合方法研究了复合材料加筋壁板的抗鸟撞性能。鸟撞方式包括垂直冲击和斜冲击两种,复合材料的冲击损伤模型采用Chang-Chang模型,分析了三种鸟撞速度下鸟撞性能参数如复合材料壁板的失效单元数、鸟体剩余动能和筋条的变形,以及复合材料壁板和筋条在某一鸟撞速度下应力随筋条数的变化规律。计算结果表明：垂直冲击和斜冲击下复合材料加筋壁板的抗鸟撞性能不同,并非筋条越多越有利于改善抗鸟撞性能,筋条有时还可能起反作用。     

铺层顺序对预成型体搭接复合材料拉伸性能影响的仿真与验证

使用有限元理论模拟分析了几种不同铺层顺序的预成型体搭接复合材料的拉伸性能,并且使用国产碳纤维与快速固化环氧树脂制备相应的单下陷搭接试样,测试其搭接接头的拉伸性能,对有限元计算结果进行了验证。结果表明,使用有限元计算与实验方法得到的结果基本相符。有限元模拟及实验验证发现不同铺层结构的预成型体搭接复合材料有两种不同的破坏损伤模式。搭接上层板的层间剥离强度与层板本身弯曲性能共同决定了搭接接头的破坏模式及拉伸性能,两者中强度较弱的先发生破坏,导致试样失效。在预成型体搭接接头中,0°铺层越靠近搭接面,对搭接性能的影响越明显,搭接强度越高。搭接界面处纤维层之间的相对角度不同,纤维铺层刚度不同,刚度差别越大,搭接强度就越低。     

对位芳香族聚酰胺纤维/环氧树脂复合材料防弹性能及其破坏机制

为研究对位芳香族聚酰胺纤维/环氧树脂（Epoxy resin,EP）复合材料的防弹性能及其破坏机制,采用铅芯弹侵彻复合材料靶片。以对位芳香族聚酰胺纤维作增强纤维,EP作基体树脂,纳米SiO₂和聚乙烯醇缩丁醛（Polyvinyl butyral,PVB）作增韧剂,通过热压工艺制备单向（Unidirectional,UD）结构的对位芳香族聚酰胺纤维/EP复合材料靶片。研究单片纤维面密度、UD片材结构、射击角度和树脂改性对靶片防弹性能的影响;观察弹击实验后靶片的破坏形貌,分析靶片的破坏机制。研究结果表明:对位芳香族聚酰胺纤维/EP复合材料具有优异的防弹性能,随着单层纤维面密度的增大,靶片的防弹性能呈现整体上升、局部上下波动的变化趋势;铺层方式为0°/90°/0°/90°的四层单UD片材（4UD）结构的防弹性能优于铺层方式为0°/90°的两层单UD片材（2UD）结构;角度射击时,靶片的穿透比率更大,背衬凹陷深度（Back face signature,BFS）比率更小;PVB增韧改性EP提升了靶片的防弹性能;纤维拉伸变形破坏、片材分层和基体树脂碎裂是复合材料靶片主要的吸能方式。      

基于最终层失效的复合材料舱体稳健性协调优化

传统可靠性设计难以符合现代设计要求,对舱体进行稳健性优化设计,可提高其综合可靠性。基于基体破坏和纤维断裂两种失效模式,采用验算点法求解复合材料单层可靠度。基于最终层失效假设,提出把结构看作由串联子系统组成的并联系统的思想,结合材料刚度比率退化准则和单层可靠度理论,采用概率逐步失效分析方法,计算出主要失效链,从而得出结构的失效概率。复合材料舱体设计变量复杂,提出二级优化方法思想：一级为系统级布局优化,对加强筋截面形状、位置确定等参数进行优化;二级为子系统级尺寸优化,对筋截面尺寸、复合材料各铺层厚度等参数进行优化。采用自适应随机搜索遗传算法,以复合材料舱体质量最小为目标函数,以可靠度要求为约束条件,采用稳健性协调优化方法,对存在初始缺陷的复合材料舱体进行稳健性优化,为复合材料结构优化设计提供参考。     

基于材料选型优化的金属-复合材料组合结构-声辐射优化

基于金属铺层假设,以结构材料属性和材料铺层数量为设计变量,建立了基于金属-复合材料的材料选型结构-声辐射优化设计模型。以钢-纤维增强复合材料组合结构为例,开展了多设计变量、多约束条件的结构-声辐射优化研究。最后,采用遗传算法进行求解,实现了结构材料的转换。数值算例表明,通过金属-复合材料组合结构的材料选型优化,可以有效降低钢-纤维增强复合材料结构的振动和声辐射。文中的研究方法为结构材料的分布优化提供了一种可行有效的思路。     

复合材料雷达罩鸟撞破坏的流固耦合动响应分析

建立了鸟撞复合材料雷达罩有限元模型,用壳单元模拟雷达罩,在鸟体周围附加用于模拟空气的欧拉流动域,利用显示动力分析软件LS-DYNA对鸟撞复合材料雷达罩的过程进行了数值模拟,对雷达罩的破坏响应进行了分析。结果表明,在撞击的过程中,应力的峰值主要出现在被撞击区域的周围;部分区域的不同材料层间会承受不同的应变趋势。     

基于非线性本构关系的复合材料风机叶片有限元极限分析与设计

为了研究具有三维复杂构形的复合材料风机叶片的逐次破坏过程和极限承载能力, 将复合材料细观力学非线性本构理论桥联模型与有限元软件ABAQUS通过用户子程序UGENS结合起来对风力发电机叶片结构进行极限强度分析。只需提供纤维和基体的材料性能参数、 纤维体积含量以及蒙皮和增强筋的铺层数据包括铺设角、 层厚和铺层数, 就可预报出复合材料复杂叶片结构的整体承载能力以及叶片破坏所处的位置, 为正确评估和合理设计风机叶片结构提供了一种简便有效的分析方法。以一种20kW风机叶片为例, 用此方法实现了新型复合材料叶片结构的极限分析和合理设计, 提高了叶片的强度和刚度, 有效降低了叶片的重量。本文中的方法同样适用于其它复合材料复杂结构的极限分析与强度设计。      

不同结构UHMWPE纤维纬编针织复合材料弯曲性能

以超高分子量聚乙烯(UHMWPE)纤维为原料,在电脑横机上编织出较理想的UHMWPE纤维纬平针、罗纹、畦编针织结构织物.采用VARTM工艺、(0°,90°)3s铺层方式成功制备了六层纬平针、六层罗纹以及六层畦编UHMWPE纤维纬编针织复合材料板.对三种复合材料板的弯曲性能及其影响因素进行研究,比较并分析其弯曲应力-挠度变化曲线和破坏形式.结果表明:三种UHMWPE纤维纬编针织结构增强复合材料的弯曲应力-挠度曲线具有非线性特征,曲线均类似于抛物线;其中,纬平针织结构复合材料的弯曲强度最大,罗纹次之,畦编最小;承受弯曲破坏的主要是树脂基体,没有出现增强体断裂、撕开等现象,表明由高强聚乙烯纤维制成的增强体材料具有较强的韧性与较高的强力.     

SPH – Lagrangian study of bird impact on leading edge wing

Experimental bird-strike tests were conducted using a dead chicken of 8lb with a speed of 250kts that hit on leading edge bay in composite material made with aluminium alloy 2024-T3, core panel of honeycomb and GLARE cover plates. A validated simulation methodology has been developed in order to use a reference in further bird test certification procedure on the fin of the C27-J aircraft.     

Bird-strike simulation for certification of the Boeing 787 composite moveable trailing edge

A validated simulation methodology has been developed to support the bird-strike certification of the carbon fibre epoxy composite, moveable trailing edge (MTE) of the Boeing 787 Dreamliner. The explicit finite element software PAM-CRASH™ was selected to perform the simulations utilising the advanced composite material, fastener and smooth particle hydrodynamic bird models available in the code. The modelling procedures were validated firstly through comparison with existing test data and secondly through the testing and analysis of representative structures. Subsequent use of the validated modelling procedures during the analysis of the MTE facilitated the evaluation of numerous bird-strike scenarios, leading to improved design efficiency and safety, while significantly reducing certification costs.     

Finite-element simulation for modeling composite plates subjected to soft-body,high-velocity impact for application to bird-strike problem of composite fan blades

We presented a numerical simulation to address the impact-induced deformation and damage of composite plates subjected to soft-body, high-velocity impacts for application to the bird-strike problem of composite fan blades. A new stabilized contact algorithm was developed based on the Lagrange multiplier method to predict appropriate impact forces applied to the plate, in order to solve soft-body impact at high velocity without causing severe numerical instabilities. The bird-strike impact on composite fan blade was simply modeled by discussing the damage characteristics of a unidirectional composite plate. Combining the model of a soft-body impactor with an appropriate contact algorithm, we could capture the transition from the global bending mode at low velocity to the local deformation mode at high velocity, enabling a discussion of the ballistic limit using the damage analysis of the laminate. As the impact velocity increased, the damage in the composite changed from bending-induced matrix-cracking to an intensive fiber-breakage mode causing local shear perforation. The damage mode transition allows us to detect the transition velocity as a ballistic limit, which is one of the critical factors for discussing the bird-strike resistance of composite fan blades.     

Numerical simulations of low-velocity impact on an aircraft sandwich panel

The potential hazards resulting from a low-velocity impact (bird-strike, tool drop, runway debris, etc.) on aircraft structures, such as engine nacelle or a leading edge, has been a long-term concern to the aircraft industry. Certification authorities require that exposed aircraft components must be tested to prove their capability to withstand low-velocity impact without suffering critical damage.

This paper describes the results from experimental and numerical simulation studies on the impact and penetration damage of a sandwich panel by a solid, round-shaped impactor. The main aim was to prove that a correct mathematical model can yield significant information for the designer to understand the mechanism involved in the low-velocity impact event, prior to conducting tests, and therefore to design an impact-resistant aircraft structure.

Part of this work presented is focused on the recent progress on the materials modelling and numerical simulation of low-velocity impact response onto a composite aircraft sandwich panel. It is based on the application of explicit finite element (FE) analysis codes to study aircraft sandwich structures behaviour under low-velocity impact conditions. Good agreement was obtained between numerical and experimental results, in particular, the numerical simulation was able to predict impact damage and impact energy absorbed by the structure.     

简谐激励下阻尼复合结构多尺度拓扑优化设计

目的 为得到抗振性能良好的板壳结构,保证设备的正常工作,文中提出一种板壳阻尼复合结构多尺度优化设计方法。方法 以动柔度为目标,建立频域激励下和固定频率点激励下板壳阻尼复合结构中阻尼材料宏观分布和微结构协同设计的多尺度问题的数学模型,推导目标函数和约束条件对设计变量的灵敏度,并基于移动渐近线法求解优化数学模型。结果 所提多尺度设计方法可以有效获得板壳结构最优阻尼材料宏观布局和最优阻尼复合材料微结构构型,提高了结构的动力学性能,同时结果也表明涂敷阻尼复合材料结构的振动响应相较于仅涂敷单一阻尼材料的振动响应大幅减小。结论 研究表明,不同激励频率下阻尼材料的宏观分布形态不同,阻尼材料主要分布于结构模态振型位移的最大处和支撑端,通过加强结构的刚度,抑制了结构变形,减小了振动响应。微结构构型基本类似,其基本形态都是低刚度、高阻尼材料呈条状分布,条状分布的阻尼复合材料微结构在受弯方向上的刚度较大,可以有效抵制结构的弯曲变形。     

Modelling of Bird Strike on an Aircraft Wing Leading Edge Made from Fibre Metal Laminates – Part 2: Modelling of Impact with SPH Bird Model

Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts such as runway debris or bird strikes. In a collaborative research project, aircraft wing leading edge structures with a glass-based FML skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element model is developed for simulating the bird strike tests, using Smooth Particle Hydrodynamics (SPH) for modelling the bird and the material model developed in Part 1 of the paper for modelling the leading edge skin. The bird parameters are obtained from a system identification analysis of strikes on flat plates. Pre-test simulations correctly predicted that the bird did not penetrate the leading edge skin, and correctly forecast that one FML lay-up would deform more than the other. Post test simulations included a model of the structure supporting the test article, and the predicted loads transferred to the supporting structure were in good agreement with the experimental values. The SPH bird model showed no signs of instability and correctly modelled the break-up of the bird into particles. The rivets connecting the skin to the ribs were found to have a profound effect on the performance of the structure.     

Analysis of Bird Impact on a Composite Tailplane Leading Edge

One of the main structural requirements of a leading edge of a tailplane is to ensure that any significant damage caused by foreign object (i.e. birdstrike, etc...) would still allow the aircraft to land safely. In particular, leading edge must be certified for a proven level of bird impact resistance. Since the experimental tests are expensive and difficult to perform, numerical simulations can provide significant help in designing high-efficiency bird-proof structures. The aim of this research paper was to evaluate two different leading edge designs by reducing the testing costs by employing state-of-the-art numerical simulations. The material considered was a sandwich structure made up of aluminium skins and flexcore as core. Before each test was carried out, pre-test numerical analyses of birdstrike were performed adopting a lagrangian approach on a tailplane leading edge of a large scale aircraft using the MSC/Dytran solver code. The numerical and experimental correlation have shown good results both in terms of global behaviour of the test article and local evolution of some measurable parameters confirming the validity of the approach and possible guidelines for structural design including the bird impact requirements.     

射流侵彻截面为六边形的液态复合密闭结构力学特点仿真分析

截面为六边形的液态复合密闭结构抗射流侵彻性能与其受力变形、应力、应变、能量变化息息相关。为了解密闭结构受射流侵彻的力学特点,采用理论分析与数值仿真相结合的方法,开展了研究。理论分析中,推导了射流的剩余头部速度;分析了密闭结构的受压情况,密闭结构微元的柯西(Cauchy)应变、格林(Green)应变、本构关系,侵彻系统的能量变化。数值仿真结果表明:射流侵彻进入液态复合密闭结构后,面板的等效应力从内到外呈环状逐渐递减;竖壁面的等效应力从上到下逐渐增大,在棱边上衰减,在底部集中;射流带动液体运动,进一步扩大背板孔口,并导致液体出现壅塞而产生逆流,使竖壁面产生附加应变;冯?米塞斯(Von Mises)应变集中在液态复合结构孔壁上,Green等效应变集中在密闭结构底部的内棱边上、以及面板和背板的孔口处;射流25 μs时开始侵彻液态复合密闭结构,射流、密闭结构、液体的能量均发生明显变化。