航空铝合金力学与电化学耦合点蚀损伤模型研究

点蚀是航空铝合金材料在服役环境下常见的损伤形式,点蚀损伤会导致材料性能的下降, 严重地威胁着结构的承载能力。作为承力构件,航空铝合金不仅承受环境腐蚀的作用,还承受应力作用。论文根据点蚀基本原理,引入细观损伤变量孔隙率,考虑力学化学效应,建立了点蚀损伤弹性模量计算模型。使用2219铝合金,进行加速腐蚀试验和单向拉伸试验,利用显微扫描技术研究了点蚀坑深度随时间和载荷的变化,并对腐蚀后试验件的损伤宏观形貌进行观察分析。根据拉伸实验结果,对模型的正确性进行验证。模型计算与实验结果的对比证明了本文方法的可行性与正确性。     

结构健康监测技术及其在航空航天领域中的应用

对飞行器结构中的裂纹、腐蚀、脱层、材料性能退化及其它损伤进行及时且准确的检测是确保服役飞行器安全可靠运行的必要手段。结构健康监测是确定结构完整性的革命性创新技术,它在飞行器的结构设计、飞行及维护过程中都可发挥重要作用,它的使用可以提高飞行安全性、降低维护成本。本文简要介绍结构健康监测的系统组成、基本原理及关键技术,并通过实例阐述了基于智能层的结构健康监测技术在飞行器上的应用情况。     

Evaluation of atmospheric corrosion damage to steel space structures in coastal areas

Steel space structures in coastal areas, often exposed in the open air, are inevitably subjected to atmospheric corrosion. This paper presents a framework for evaluation of potential damage due to atmospheric corrosion to steel space structures in coastal areas through an integration of knowledge in material science and structural analysis. An empirical model for estimating corrosion of steel material is first presented based on long-term experimental data available. Equations relating structural natural frequency sensitivity to structural member thickness are then derived in consideration of both inner and outer surface corrosions of the structural member. The nonlinear static analysis is finally conducted to evaluate effects of atmospheric corrosion on the stress of structural members and the safety of steel space structures. By taking a real large steel space structure built in southern coastal area in China as example, the feasibility of the proposed approach is examined and the potential damage caused by atmospheric corrosion to the structure is assessed. The results demonstrate that the atmospheric corrosion does not obviously affect the natural frequencies of the structure but it does create stress redistribution and some of the structural members may have large stress changes.     

THREE-DIMENSIONAL CELLULAR AUTOMATA MODEL FOR PREDICTING LOCAL CORROSION

针对环境作用下金属表面容易形成坑蚀而致使结构性能退化这一问题. 采用元胞自动机方法，建立描述腐蚀环境中金属表面坑蚀形成及演化的三维模型，对不同腐蚀溶液浓度和温度条件下结构表面蚀坑随时间的变化过程进行了模拟，为定量评估服役环境中结构的剩余强度及寿命提供可能.     

复合材料修补结构腐蚀扩展特性实验研究

为了研究腐蚀环境对复合材料修补结构疲劳特性的影响,开展以某型飞机加速环境谱为基础的预腐蚀试验,并采用递进式的试验方法分别完成对未修补未腐蚀、修补但未腐蚀、又修补又腐蚀的试样疲劳裂纹扩展试验。利用试验数据计算了复合材料修补构型、腐蚀环境对裂纹尖端应力强度因子影响的修正系数,并确定了通过试验验证的修补结构疲劳裂纹扩展修正模型。该模型预测腐蚀环境下修补结构的疲劳寿命与试验值一致。试验数据和预测模型可为海军飞机复合材料修补结构的损伤容限设计提供参考。     

Peridynamic modeling of pitting corrosion damage

In this paper we introduce a peridynamic model for the evolution of damage from pitting corrosion capable of capturing subsurface damage. We model the anodic reaction in corrosion processes (in which electroplating is negligible) as an effective peridynamic diffusion process in the electrolyte/solid system coupled with a phase-change mechanism that allows for autonomous evolution of the moving interface. In order to simulate creation of subsurface damage, we introduce a corrosion damage model based on a stochastic relationship that connects the concentration in the metal to the damage of peridynamic mechanical-bonds that are superposed onto diffusion-bonds. We study convergence of this formulation for diffusion-dominated stage. The model leads to formation of a subsurface damage layer, seen in experiments. We validate results against experiments on pit growth rate and polarization data for pitting corrosion. We extend the 1D model to the 2D and 3D, and introduce a new damage-dependent corrosion model to account for broken mechanical bonds that enhance the corrosion rate. This coupled model can predict the pit shape and damage profile in materials with microstructural heterogeneities, such as defects, interfaces, inclusions, and grain boundaries.     

Composite patch reinforcement of cracked aircraft upper longeron: analysis and specimen simulation

The use of composite patches on cracked portions of metallic aircraft structures is an accepted means of improving fatigue life and attaining high structural efficiency. As more and more advanced composite materials are beng developed, the wider use of the repair technology is anticipated even for the reinforcement of primary aircraft structure. The objective of this work is to illustrate how the composite patch repair technology can be successfully applied to restore the structural integrity of cracked components.The Phosphoric Acid Anodize (PAA) surface treatment on aluminum when applied in conjunction with the AVI13/HV998 adhesive were essential for achieving the appropriate patch bonding strength. Such a process was done without immersing the component into the PAA tank; dismantling the component from the aircraft was not necessary. Boron/epoxy and carbon/epoxy patches were applied at room temperature to the 7075-T6511 cracked specimens and tested under fatigue simulating the load spectrum for the upper longeron attached to the access door of the electronic equipment bay. Considerable improvement in the fatigue life was observed after the repair. Equivalent flight test hours were increased from approximately two thousand hours at which the component fractured completely when not repired to twelve thousand hours when the repair was made with only a small amount of crack growth. A six times increase fatigue life is obtained. The laboratory developed technique has been applied to several in-service aircraft which have now been flown for more than 700 h without detection of crack growth.     

爆炸载荷下飞机典型加筋结构毁伤特性

为了探讨爆炸载荷下飞机典型加筋结构的响应规律,开展了爆炸实验,获得了飞机典型结构表面的反射超压历程,加筋结构的应变、位移等结构响应数据。并结合实验结果建立了高置信度的有限元模型,研究了所选结构的变形分布规律和塑性毁伤特性。结果表明,对于本文中选取的飞机加筋结构,塑性变形除了会开始于常见的加强筋中点外,还会开始于加强筋与加强筋联结处、加强筋与外框联结处。这主要是受加筋板的双向拉伸变形和应力集中的影响。进一步总结了随冲击波正压时间增长,能够引发加筋结构塑性变形的有效冲量和反射超压峰值阈值。研究结果对飞机气动外形、抗爆能力设计具有重要意义。     

民机复合材料结构冲击后压缩设计值的确定方法

冲击后压缩设计许用值是复合材料飞机结构设计的一个非常重要的参数。本文通过分析常用的目视检测方法和飞机结构冲击能量统计结果,从凹坑深度和冲击能量截止值两方面定义了目视勉强可见损伤;根据民机设计兼顾安全性和经济性的特点,作者提出压缩设计许用值中的目视勉强可见损伤应综合考虑,慎重确定。文章还研究了复合材料层压板的抗冲击性能,从工程应用角度给出了结构冲击后压缩设计许用值的确定要点,即用小试样的冲击后压缩试验结果推导的基准系数和环境系数,对元件乃至典型结构件的冲击后压缩试验结果进行修正。     

单轴压缩条件下溶蚀礁灰岩细观变形破坏特征研究

礁灰岩的溶蚀对海洋工程和岛礁工程的稳定性有明显的影响.孔隙型溶蚀是礁灰岩常见的溶蚀方式.本文通过构建随机溶蚀孔洞的离散元模型,模拟孔洞型溶蚀礁灰岩的细观变形破坏特征,分析其变形破坏规律与裂隙演化特征.结果 表明,基于随机聚类算法构建的溶蚀礁灰岩离散元模型能够很好地模拟孔洞型溶蚀作用,且其变形破坏特征具有明显的规律;随着...     

民机复合材料结构修理容限研究

论文对民用飞机复合材料结构的修理容限进行了研究.在分析相关概念的基础上,根据结构对飞机安全性的重要性对损伤部件进行分类,并用损伤检出概率来衡量损伤程度,对结构承载能力要求进行线性划分.接着在深入分析波音飞机公司修理指标的基础上,提出了修理容限量化的评估指标,为修理方案的制定和优化提供技术依据.最后介绍了结构修理评估及附加检查.     

热端部件低温热腐蚀疲劳损伤机理、寿命模型和抗腐蚀设计方法

对于沿海地区或海洋环境中使用的航空发动机来说,由于高温、机械载荷和盐雾环境的共同作用,热腐蚀疲劳破坏是影响其热端部件服役寿命的主要因素.本文对热端部件低温热腐蚀疲劳损伤机理、寿命模型和防腐蚀设计方法进行了总结、归纳及评述,提出了未来的研究趋势与发展方向.首先介绍航空发动机热端部件的热腐蚀疲劳故障案例、损伤演化机理;其次,重点分析了低温腐蚀疲劳寿命的唯象模型、损伤力学模型、断裂力学模型以及机器学习模型;再次,对几种代表性的考虑腐蚀演化不同阶段的分段式腐蚀疲劳全寿命模型进行综述,还分析指出了腐蚀疲劳全寿命模型的发展趋势;从次,对航空发动机材料选择、零件制造、结构强度设计和外场运行维护不同阶段的抗腐蚀方法进行了综述.最后,对增材制造零部件的热腐蚀疲劳问题以及无损检测技术、人工智能等与热腐蚀疲劳研究的结合进行了展望.     

A new nonlinear elastic time reversal acoustic method for the identification and localisation of stress corrosion cracking in welded plate-like structures – A simulation study

In order to reduce the costs related to corrosion damage in aircraft structures, it is vital to develop new robust, accurate and reliable damage detection methods. A possible answer to this problem is offered by newly developed nonlinear ultrasonic techniques, which monitors the nonlinear elastic wave propagation behaviour introduced by damage, to detect its presence and location.In this paper, a new nonlinear time reversal technique is presented for the detection and localization of a scattered zone (damage) in a multi-material medium. In particular, numerical findings on a friction stir-welded aluminium plate-like structure are reported. Damage was introduced in the heat affected zone and modelled using a multi-scale material constitutive model (Preisach–Mayergoyz space).Studies were conducted for two different transducer configurations. Particular attention was devoted to find the optimum time-reversed window to be re-emitted in the structures. The methodology was compared with traditional time-reversal acoustics (TRA), showing significant improvements. While the traditional TRA was not able to clearly localise the damage, the developed technique identified in a clear manner the faulted zone, showing its robustness to locate and characterize nonlinear sources, in presence of a multi-material medium.     

鸟体姿态对结构抗鸟撞性能的影响

低于现行标准规定能量的大量鸟撞事故中,航空结构仍然发生实质性破坏的情况,说明只考虑鸟体的质量和速度不足以保证飞机安全。本文中针对弹性平板、雷达罩及机翼前缘等飞机典型结构,开展了不同姿态鸟体的鸟撞分析研究。分析结果发现,鸟体姿态对结构的抗鸟撞性能有比较显著的影响,不同的结构特点反映的响应规律也不同:对吸能结构,姿态角越大,吸收的能量越多,被保护的结构就越安全;而对承力结构,姿态角越大,高应力区域越大,结构就越危险。因此,在结构的抗鸟撞安全性评估中,除了完成特定姿态鸟体的鸟撞实验,针对危险工况还应通过数值分析评估不同鸟体姿态的结构撞击响应,进一步确保结构的抗鸟撞能力。     

飞行器非线性气动伺服弹性力学

现代飞行器日益呈现结构轻质化、控制系统宽通带和高权限的发展趋势. 因此, 非定常气动力、柔性结构和主动控制系统三者间的耦合力学成为重要的研究领域. 自20世纪80年代起, 航空界开始关注受控飞行器的气动弹性稳定性以及主动控制问题, 但对气动/结构的非线性效应、控制回路时滞对受控飞行器动力学行为的影响规律研究尚不充分. 研究这些影响规律不仅涉及非线性、高维数、多变参数和时滞效应等难题, 而且必须面对空气动力、飞行器结构、驱动机构、控制系统之间的强耦合问题. 其中的前沿难题是: 发展非线性气动伺服弹性动力学建模理论, 揭示上述因素诱发受控气动弹性振动的动力学机理, 开展气动伺服弹性控制风洞实验. 本文针对非线性气动伺服弹性力学所涉及的非线性非定常气动力建模、非线性结构动力学、气动伺服弹性控制律设计、气动伺服弹性实验, 总结相关研究现状和最新进展, 特别是近年来作者学术团队的研究成果, 并对进一步研究给出若干建议.      

Mesoscopic model to simulate the mechanical behavior of reinforced concrete members affected by corrosion

In this contribution, a finite element methodology devised to simulate the structural deterioration of corroded reinforced concrete members is presented. The proposed numerical strategy has the ability to reproduce many of the well-known (undesirable) mechanical effects induced by corrosion processes in the embedded steel bars, as for example: expansion of the reinforcements due to the corrosion product accumulation, damage and cracking patterns distribution in the surrounding concrete, degradation of steel–concrete bond stress transfer, net area reduction in the reinforcements and, mainly, the influence of all these mentioned mechanisms on the structural load carrying capacity predictions.At the numerical level, each component of the RC structure is represented by means of a suitable FE formulation. For the concrete, a cohesive model based on the Continuum Strong Discontinuity Approach (CSDA) is used. Steel bars are modeled by means of an elasto-plastic constitutive relation. The interface is simulated using contact-friction elements, with the friction degradation as a function of the degree of corrosion attack. Two different (and coupled) mesoscopic analyzes are considered in order to describe the main physical phenomena that govern the problem: (i) an analysis at the cross section level and (ii) an analysis at the structural member level.The resultant mechanical model can be used to simulate generalized reinforcement corrosion. Experimental and previous numerical results, obtained from the available literature, are used to validate the proposed strategy.     

含广布腐蚀坑结构寿命评估方法

为了定量评估含广布腐蚀损伤老龄化飞机结构的剩余强度, 采用等效裂纹方法将腐蚀坑沿垂 直于外界最大主应力方向进行投影处理, 使其转化为具有相同寿命的等效初始表面裂纹, 然 后采用参数化有限元方法,求解等效裂纹前沿的应力强度因子、裂纹扩展方向和裂纹扩展增量, 建立并应用应力强度因子变化历程, 采用循环接循环的损伤累积方法对含广布等效表面裂纹 在疲劳载荷作用下的寿命进行了预测. 预测结果为复杂环境中含广布腐蚀坑的飞机结构寿命 预测提供了参考.     

Evaluation of Methodologies to Accelerate Corrosion Assisted Fatigue Experiments

The corrosive nature of a marine environment is an important factor to be considered during the fatigue design of offshore structures. Thereto S-N curves must be determined in close to real conditions which is highly time consuming. It is hypothesized that if the corrosion process is accelerated at approximately the same rate as the fatigue frequency, testing time could be highly reduced. Corrosion acceleration is possible by modifying physical and/or electrochemical properties involved in the redox reactions. In this work the first option was chosen. Based on a literature review temperature and dissolved oxygen level were concluded to be the most influencing parameters. Several test scenarios with different combinations of sea water temperature and dissolved oxygen level have been defined. Corresponding S-N curves have been constructed for HSLA steel (type DNV F460) specimens immersed in natural seawater. The direct current potential drop technique was used to quantify damage evolution for all tested scenarios. Additionally, a reference S-N curve for immersed behaviour was determined at a temperature and frequency close to North Sea conditions. Comparison of the experimental results indicates that an average acceleration of the corrosion assisted fatigue damage process of around 80 % could be obtained.     

Interaction of ultrasonic waves with structural damage: A diffraction analogy

This study investigates the interaction of ultrasonic waves and structural damage, i.e., cracking and corrosion. It is shown that cracking and corrosion damage produces a diffraction pattern that resembles that associated with the traditional physics of wave motion. The extension of this hypothesis implies that it may be possible to use a simple ripple tank to investigate how to best detect/sense and size a given damage state, e.g., corrosion. We also find that cracking, and corrosion damage, has a significant effect on both the amplitude and period of the waveform and also on the local (apparent) refractive index of the material and that these effects have the potential to be used as damage indicators.     

大飞机研制中的若干复合材料力学问题

简要介绍了先进复合材料在当代大型飞机结构中的应用状况,以及相关的力学问题,着重论 述了复合材料及结构的工艺力学、跨尺度材料/结构一体化设计问题和力学性能表征、高效复 合材料结构设计和力学分析、复合材料损伤容限与耐久性设计、大型飞机的安全监测和管理 系统等. 指出,从目前国际上以及我国复合材料在大型飞机结构上的应用趋势来看,我们需 要进一步发挥广大力学工作者与相关领域科研人员和工程师的协同作用,提高我国复合材料 基础研究和应用水平,使复合材料在提升我国研制的大飞机的先进性和竞争力方面发挥重要 的作用.