关键词： 复合材料   固化变形   装配间隙   热力耦合前处理法   机械连接强度  

摘要： 固化变形会引起装配间隙，从而对复合材料搭接结构连接强度造成影响。为研究固化变形引起的装配间隙对复合材料搭接结构连接强度的影响，提出热力耦合前处理法，针对于复合材料单搭接结构，建立含孔层合板模型进行热—力耦合分析，得到含固化变形的带孔层合板模型，并在该模型的基础上建立含装配间隙的复合材料单搭接结构模型，进行拉伸试验的数值模拟，得到复合材料单搭接结构的拉伸强度，并与不含固化变形的复合材料单搭接结构的拉伸强度进行对比，分析固化变形对复合材料机械连接强度的影响。结果表明：使用本文提出的热力耦合前处理法进行强度预测，结构拉伸极限强度减少约3.2%。

关键词： SPFRAG新型材料   超精密磨床   性能参数测试   热膨胀系数   热稳态分析   瞬态热应力   热结构耦合   热稳定性  

摘要： 针对传统铸铁材料磨床床身存在温度分布不均、温度波动范围广、热应力和热变形大、较难达到热平衡等问题，提出采用钢-聚丙烯纤维增强人造花岗岩材料（SPFRAG）代替铸铁材料来改善床身热稳定性能。研究并设计SPFRAG各组分材料的配比和制备工艺，研制综合性能较佳的SPFRAG新型材料成型试件，并测试该材料的静态机械强度以及热性能参数，与铸铁材料的属性参数进行对比分析。以某型号铸铁材料磨床床身为设计原型，优化SPFRAG新型材料超精密磨床床身新构型，充分利用Solid Works与ANSYS Workbench软件联合仿真模拟的优势，分析机床整机在工作状态下影响SPFRAG新型材料磨床床身变形的多处热源，确定床身边界条件，对SPFRAG新型材料磨床床身进行有限元热稳态以及瞬态热应力分析，研究SPFRAG新型材料磨床床身不同位置温度大小对其结构热变形的影响，并对该材料磨床床身热态性能结果进行比较分析。研究结果表明：SPFRAG新型材料磨床床身表面具有较小的温度梯度分布，温度波动范围小且达到热平衡时间短，导轨面和电机安装面为温升最高部位，其余部位温度变化不大。在仿真实验条件下，SPFRAG新型材料磨床床身由于温度分布不均和温度梯度产生的瞬态热应力和瞬态热变形量均较小，热环境下磨床床身前几阶固有频率均有显著提高，同时热膨胀系数的下降可进一步降低磨床床身热变形，其中，相较于原型铸铁材料磨床床身，优化后的SPFRAG新型材料磨床床身热变形降低12.56%、热应力降低67.88%，磨床床身前三阶固有频率提升幅度分别为27.72%、53.48%、33.76%。以上研究结论充分说明SPFRAG新型材料在提高磨床床身热性能以及热稳定性等方面的可行性和优越性。最后针对降低磨床床身热变形以及提升机床生产可靠性提出相应的解决措施，可为提高机床加工精度提供依据。

关键词： CFRP   电偶腐蚀   腐蚀机制   防护技术   表面处理  

摘要： 碳纤维增强树脂基复合材料（CFRP）具有比强度高、比模量高、耐疲劳性优良、性能可设计和易于整体成型等许多优异特性，已广泛用于航空航天和各种武器装备。其中，CFRP与金属材料组成的混合结构适可用于多种复杂严苛的环境，具有广泛的应用前景。然而，在实际使用中，CFRP不可避免地会与金属材料接触，由于CFRP具有较高的电极电势，与金属材料连接后，金属材料往往作为阳极发生加速腐蚀，从而引发电偶腐蚀问题。这种电偶腐蚀已成为以碳纤维增强树脂基复合材料（CFRP）为核心的现代宽体飞机结构面临的重大风险之一。因此，深入研究CFRP与金属间的电偶腐蚀行为，不仅能够为CFRP材料的设计与优化提供科学依据，还对其工程化应用具有重要意义。随着面向结构风险评估和防护系统设计的研究持续开展，CFRP与金属间的电偶腐蚀在腐蚀机制和防护技术领域的研究成果大量涌现。本文围绕CFRP为阴极的电偶腐蚀问题，对CFRP/金属间电偶腐蚀研究方法，影响电偶腐蚀的因素和腐蚀防护技术等方面的成果进行了综述。

关键词： Pickering双乳液   文冠果油   纳米纤维素   稳定性   激光扫描共聚焦显微镜  

摘要： 基于文冠果油和纳米纤维素开发W1/O/W2型Pickering双乳液体系，并评价其稳定性。以1%（W/V）海藻酸钠为内水相(W1)，聚甘油蓖麻醇酸酯为内层界面乳化剂，文冠果油为中间油相，纳米纤维为外层乳化剂，整个乳液体系分散于外水相(W2)中。以双乳液微观结构、表观粘度、热稳定性、离心稳定性、冻融稳定性、外观分层为评价指标，分别比对了不同聚甘油蓖麻醇酸酯浓度、内水相(W1)与油相（O）体积比、初乳液(W1/O)与外水相(W2)体积比、纳米纤维素的种类及添加量等5种因素对双乳液体系的影响。通过扫描电子显微镜和接触角测量仪发现不同种类纳米纤维素的微观结构和疏水性差异明显，其中长径比大且成网状结构的纤维素纳米纤维疏水性最强。当聚甘油蓖麻醇酸酯浓度为2.5%（W/V），W1:O为3:7（V/V），(W1/O):W2为2:8（V/V），纤维素纳米纤维作为外层乳化剂的浓度为0.3%（W/W）时，双乳液的包埋率高且稳定性强。相对于纤维素纳米晶，纤维素纳米纤维所制备的双乳液稳定性更强。激光扫描共聚焦显微镜观察表明双乳液构建成功且结构稳定。油脂的酸价及过氧化值进一步反映了双乳液的化学稳定性。以纳米纤维素的固体微颗粒为乳化剂，文冠果油为包埋油相的Pickering双乳液，可作为一种新型功能性成分的良好递送载体。

关键词： 改进的灰狼优化算法   石墨烯纳米片   孔隙   功能梯度材料   颤振  

摘要： 本文探讨了石墨烯增强功能梯度多孔层合壳在气流和热荷载作用下的颤振优化问题。通过引入非线性收敛因子和自适应调整机制，对传统灰狼优化算法进行了精细化改进，以结构重量与固有频率的比值为优化目标，以半锥角、层数和孔隙体积分数为优化变量，通过改进的灰狼优化算法，获得了最优设计参数，并以颤振临界速度作为评估结构动力稳定性的指标。研究结果显示，改进的灰狼优化算法具有更强的全局搜索能力和更高的求解精度；若环境温度从500K降低至400 K、石墨烯质量分数从0%增至2%以及长径比从6.0减至4.0时，颤振临界速度分别提高了25%、12%和23%；此外，石墨烯与孔隙的分布及含量对最优层数有显著的影响，边界条件、环境温度及长径比等外部因素对壳体最优半锥角和层数的影响则较小，但它们对最优孔隙体积分数的影响却不容忽视。

关键词： 玄武岩纤维   分散性能   树脂浸渍   纸基材料   光伏背板  

摘要： 玄武岩纤维具有优异的力学性能、绝缘性能和绿色环保等优点，然而化学惰性和较差的分散性限制了它在纸基材料领域的应用。以玄武岩纤维、芳纶浆粕为原料，通过湿法造纸、浸渍热压工艺制备玄武岩纤维纸基复合材料，系统地对玄武岩纤维的分散性能及其纸基复合材料的制备工艺进行了研究。结果表明，玄武岩纤维在2.9 mol·L-1、51 ℃的盐酸溶液中前处理改性14 h后，又在纤维浓度、电导率、水温、pH值分别为0.8 wt‰、2.0 μS·cm-1、60 ℃、3的水环境中进行分散，同时加入6.0 wt%的分散剂羧甲基纤维素钠，其纤维分散度从60.4%提至88.43%，与芳纶浆粕按比例5:5混抄的纸页抗张指数提高了2.4倍；芳纶浆粕的加入提升了玄武岩纤维纸的强度和绝缘性能；玄武岩纤维纸浸渍5.0 wt%的酚醛树脂，经两段固化后得到玄武岩纤维纸基复合材料，各项性能显著提高，其中抗张指数和击穿强度对应提高了105.85%、54.10%。本研究为拓宽玄武岩纤维的应用领域，及实现功能化玄武岩纤维纸基复合材料在光伏背板上的应用提供了一种新的思路。

关键词： Picosecond lasers  

摘要： In the field of aerospace defense, 2.5D C/SiC composites are crucial materials for high-temperature resistant components. The high hardness and wear resistance of these materials render the high-quality micro-hole machining exceptionally challenging. A picosecond laser drilling process for 2.5D C/SiC composites based on magnetic field/liquid-assisted machining (MLM) was proposed. By extracting the characteristics of micro-hole inlet/outlet diameter, taper, oxidation, and recast layer, a comparative study was conducted between MLM and three processes: picosecond laser machining (PM), magnetic field-assisted machining (MM), and liquid-assisted machining (LM). The results demonstrate that the picosecond laser machining based on MLM can effectively reduced the inlet diameter of the micro-holes while increasing the outlet diameter, achieving a micro-hole taper of 1.3° and 1.1° under two different sets of experimental parameters, the taper is reduced by 18.75% and 45% compared with PM process, reduced by 13.33% and 31.25% compared with MM process, reduced by 91.22% and 79.63% compared with LM process, respectively. Furthermore, microstructural analyses of the drilled micro-holes were performed using EDS spectroscopy, Raman spectroscopy, and XPS techniques. It was found that the MLM process more effectively reduced the graphitization defects on the hole walls. Among them, liquid-assisted machining avoids oxidation at the inlet of micro-holes, while clearly observing exposed fibers and matrix, effectively avoiding thermal damage and recast layer defects. In picosecond laser drilling, the primary mechanisms of MLM are attributed to the cooling effect of the liquid, its ability to isolate oxygen, and the longitudinal stretching of the plasma by the magnetic field, which reduces the plasma shielding effect. © 2025 Aeronautical Manufacturing Technology Magazine Office. All rights reserved.

关键词： Corrosion resistance  

摘要： Continuous fiber reinforced polymer composites (CFRPCs) is a new material in the field of additive manufacturing. Compared with traditional machining materials such as metals and ceramics, CFRPCs have the characteristics of light weight, high strength, fatigue and corrosion resistance. Therefore, it is widely used in aerospace, rail transit and biomedical and other fields. In recent years, with the development of additive manufacturing technology, CFRPCs 3D printing technology has opened up new ideas for the manufacture of high performance, low cost and customizable complex structural parts. This paper presents a comprehensive review of the CFPRCs 3D printing process, focusing on the latest research advancements in materials, process parameters, and performance enhancement techniques primarily based on the fused deposition modeling (FDM) process. It concludes with a summary and outlook on the current challenges and future developments in this field. © 2025 Aeronautical Manufacturing Technology Magazine Office. All rights reserved.

关键词： Autoclaves  

摘要： The R-angle area of C-beam is prone to fold defects in the process of autoclave forming, which seriously affects the forming quality and service performance of the component. In order to accurately evaluate the degree of fold defects and provide ideas to reduce the generation of folds, C-beam samples of two different brands of prepregs at home and abroad under different layers were manufactured by using autoclaves forming process. The deformation behavior of R-angle prepregs in the forming process was analyzed and the mechanism of fold defects formation was explored. An evaluation method including thickness distribution, edge slip angle and R-angle quantitative analysis of partial folds is proposed, and the samples are evaluated and compared by using this method. The results show that the interlayer slip behavior of prepreg is the key mechanism of fold formation, and excessive slip resistance leads to fold defects. Compared with foreign prepregs, the tested domestic prepregs have greater overall viscosity, and C-beams manufactured are more prone to fold defects. The three evaluation indexes are consistent, and the degree of fold defect at R-angle of C-beam can be measured comprehensively from multiple angles. © 2025 Aeronautical Manufacturing Technology Magazine Office. All rights reserved.

关键词： Hot isostatic pressing  

摘要： The hot isostatic pressing (HIP) process of SiC/Ti60 composites was simulated using ABAQUS finite element simulation software. A representative volume element (RVE) model for SiCf /Ti60 composites with a fiber volume fraction of 25% was established to analyze the hot isostatic pressing densification process and residual stress distribution characteristics of the composites. The analysis results show that the plastic deformation and densification of the composites mainly occur during the thermal and pressure holding stages, and the thermal residual stress characteristics of the interface layer are significantly different from those of the titanium alloy matrix and SiC fibers. The circumferential stress of the TiC reaction layer in the interface layer has a sudden change compared to that of the SiC fiber, and the compressive stress value increases by about 205 MPa. The axial stress on the C-coating and TiC interface layer approaches zero, reducing the stress gradient between the SiC fiber (compressive stress) and the substrate (tensile stress). The thickness of the C layer in composite materials can affect the thermal residual stress of the interface layer. When the thickness of the C layer increases from 1.5 μm to 2.5 μm, the radial stress in the interface layer and surrounding areas decreased by 7 MPa, and the circumferential stress in the TiC interface layer decreased by 20 MPa. Increasing the holding temperature of hot isostatic pressing can enhance the densification effect, but it will slightly increase the residual stress in the interface layer and adjacent areas. © 2025 Aeronautical Manufacturing Technology Magazine Office. All rights reserved.