机翼前缘蒙皮拉形工艺参数优化与试验

飞机机翼前缘蒙皮,由于其形状和成形材料的特点使拉形结束卸载回弹后会产生较大的回弹量,对零件的成形质量影响较大。文章分析机翼前缘蒙皮零件的典型成形方案,确定主要加载轨迹参数,利用正交试验设计方法设计拉形工艺方案,通过有限元模拟和结果分析,获得了主要工艺参数对成形零件回弹量的影响规律。针对某前缘蒙皮零件,根据有限元分析结果,对工艺参数进行设计和优化,通过生产性试验,获得了成形质量较好的试验零件,并进行厚度、应变测量和对比分析,验证了有限元模拟的精度。     

基于SPH结合FEM的喷丸残余应力数值模拟

针对以往有限元模型中弹丸数量较少且为规则阵列排布的缺陷,采用光滑粒子流体动力学法(Smoothed particle hydrodynamics,SPH)与有限元法(Finite element method,FEM)相结合的方法,对喷丸过程进行数值模拟;使用MATLAB对弹丸空间位置坐标进行随机化处理,形成了大量丸粒冲击工件表面的随机喷丸仿真模型。通过分析确定了喷丸饱和时间,研究了喷射角度、弹丸流量对残余应力场的影响。结果表明:在喷丸参数一定的条件下,存在相应的饱和喷丸时间;研究喷丸参数对残余应力的影响时,应在喷丸达到饱和时间之后提取残余应力值;喷射角度增大,残余压应力增大;开始时弹丸流量增大,残余压应力会有所增大,但当其达到饱和值后,残余压应力不再变化。     

网格式高筋条整体壁板毛坯展开中结构特征映射方法研究与应用

整体壁板毛坯的合理展开对节省材料、降低成本和保证成形质量有重要意义。根据壁板零件的结构特点,壁板毛坯展开主要分为壁板外形曲面展开、结构特征映射和毛坯建模3个步骤。在采用几何模拟法实现壁板外形曲面展开的基础上,对结构特征映射的关键技术进行了研究。以某型号飞机中央翼上壁板为例,给出了毛坯展开的详细流程。     

防锈铝表面喷丸强化冲击试验研究

采用仪器化（数字化）冲击试验机，对防锈铝表面喷丸强化后进行冲击试验，试验结果表明：喷丸后的最大冲击力比母材提高35％，最大力前弹塑性变形功提高166％。     

Effectiveness of thermal shotblasting for casehardened steels

The shotpeening process that is used in industry has an ambiguous influence on the contact surface fatigue life of the casehardened steels: it improves this characteristic of the steels 12Kh2N4A and 12Kh2NVFA when using the rational hardening regime and reduces the contact surface fatigue life for any regimes of shotpeening of the temperature-resistant steel 16Kh3NVFMB-Sh. Low-temperature post-deformation annealing improves the contact surface fatigue life of both steels, but it limits their operating temperature. We can broaden the operating temperature range by the use of thermal shotblasting, which involves strain hardening of the casehardened surface that is heated to 250 °C. This is shown in the present work.Translated from Metallovedenie i Termicheskaya Obrabotka Metallov, No. 5, pp. 21–24, May, 1994.     

塑料辅助网格式整体壁板滚弯成形实验研究

文章提出一种新的壁板成形方法——填料辅助网格式整体壁板滚弯成形,即采用高精度数控机械加工技术,将等厚板加工成网格式壁板,然后在壁板的网格中加入填料,再对其进行滚弯成形,成形之后去除网格中的填料。研究了塑料填料的滚弯成形工艺,实验结果表明,塑料填料明显改善了壁板的受力状况,有效的保护了筋条,成形之后壁板的筋条没有发生失稳开裂等缺陷,且成形后壁板的直线度与弯曲度满足工艺要求。     

覆盖件拉深模压料面设计研究

以汽车覆盖件拉深工序为研究对象,利用有限元数值模拟方法,探讨了不同类型覆盖件拉深成形压料面的设计方法.结果表明：浅拉深覆盖件宜采用平压料面,能够降低拉深成形难度;深拉深覆盖件宜采用随形起伏压料面,可以保证各部分塑性变形均匀;质量要求不高的骨架类覆盖件,可将作为零件本身的翻边作为压料面的一部分.     

顶端板拉深回弹控制与影响因素分析

针对某轨道客车顶端板拉深成形存在的缺陷,运用塑性力学理论进行应力分析,提出优化补充造型和翼边反向拉深的控制方法,并运用数值模拟分析不同因素对板料拉深回弹和翘曲的影响规律。结果表明,进行板料工艺补充、增加翼边拉深工序能有效地减小端壁翘曲和拱顶外张。增大板料大曲率半径段外扩量、增大压边力和减小凹模圆角半径能有效减小端壁翘曲回弹量。控制翼边顶料板圆角半径在R4~R8mm,凸、凹模间隙在1.6~2mm,翼边压边力小于3000kN都能有效地控制板料拉深回弹。     

Pulsed eddy current detection of cracks in F/A-18 inner wing spar without wing skin removal using Modified Principal Component Analysis

Stress corrosion cracks may develop between fasteners in the aluminum inner wing spars of F/A-18 Hornet aircraft. These fasteners secure carbon-fibre/epoxy composite wing skin, of nominal 13 mm thickness, to the spar. Inspection of the spar through the wing skin is required in order to avoid wing disassembly. Pulsed eddy currents, generated by a probe design that utilizes the ferrous fastener as a flux conduit, are demonstrated as having the capability of detecting simulated cracks within the spar with the wing skin present. Differentially connected pickup coils are used to sense differences in response due to asymmetries in induced eddy current fields arising in the presence of cracks. To overcome variability in PEC signal response due to variability in magnetic coupling to the fastener, a large measurement set was analyzed using Modified Principal Component Analysis (PCA). The modified PCA minimizes residual sum of squares to extract eigenfunction scores, which are used to detect the presence of cracks ending on one side of the fastener hole. The ability of the method to sense simulated cracks independent of confounding measurement parameters was demonstrated.     

飞机蒙皮振动辅助拉伸成形工艺分析

拉伸成形结束后,由于残余应力的存在导致蒙皮零件产生较大的回弹,会严重影响蒙皮的使用质量。基于回弹产生的原因,从工件的应力-应变机制阐述了振动减小残余应力的机理,提出了一种振动辅助飞机蒙皮拉伸成形的新工艺方法,给出了该工艺的主要参数——频率、振幅在应用选择上的依据条件及实际运用中可选择的合理范围。以飞机前缘蒙皮拉伸成形为例,通过数值仿真模拟,分析了施加振动对成形蒙皮零件回弹的影响以及频率、振幅对改善回弹的影响,并通过实验加以验证。结果表明,在飞机蒙皮拉伸成形过程中,施加振动可以更加有效地减小零件的回弹,当选取的工艺参数频率为30 Hz左右、振幅在1.5 mm左右时回弹值最小,效果最佳。     

整体壁板填料滚弯成形工艺研究

整体壁板具有重量轻、结构强度高、刚性好等优点而被广泛应用于航卒航天工业.但是整体壁板的制造工艺复杂、生产周期长.为了解决这一问题,提出了一种新的成形工艺,即采用高精度数控机械加上技术将等厚板加工成网格式壁板,然后在壁板的网格中加入填料,再对其进行滚弯成形,成形之后去除网格中的填料,并研究了塑料和橡胶两种填料滚弯成形实验.实验结果表明,这种填料滚弯技术可以成形出满足工艺要求的整体壁板.     

空间曲面类复合材料构件固化变形修正软件开发

利用CATIA/CAA二次开发技术,以CATIA软件作为开发平台,开发复合材料修正软件,能够完成空间曲面类复合材料构件的固化变形修正,生成用于制造模具的工艺数模。详细介绍了软件的总体结构和各功能模块实现方法,并以机翼曲面为例进行了实验验证。实验结果表明:经过该软件的修正后,有效控制了复材构件的变形量,提高了产品精度。     

机翼整体壁板数字化制造技术

随着现代机翼整体壁板设计水平的不断提高，传统的制造模式已不能满足其制造要求。本文分析了现代机翼整体壁板制造过程，论述了现代机翼整体壁板数字化制造的优势及数字化设计、成形性评估、展开与板坯建模、喷丸路径规划与映射、辅助工艺设计等主要支撑技术，同时阐述了各支撑技术的具体关键技术。     

Numerical modeling of a wing skin peen forming process

For many years shot peering has been used to provide fatigue resistance and form to airplane wing skins at the Boeing Commercial Airplane Company. In this process, the peening intensities used to form a new wing skin have been obtained through the use of approximate geometric relationships, along with a considerable amount of trial and error testing. This paper describes a numerical model that has been applied to replicate the shot peening process used at Boeing. The model is used to predict peening intensities and the initial size of the skin (flat pattern) given an arbitrary aerodynamic contour requirement. Discussion focuses on the finite element method and special optimization techniques used in the approach.     

On the effect of the orientation of sheet rolling direction in shot peen forming

Peen forming is commonly used in the aerospace industry to shape large and thin panels, such as wing skins. This manufacturing process uses shot peening to introduce unbalanced compressive stresses near the surface of the component. These stresses tend to bend the panel and, when optimized, lead to the desired contour. Sheet materials often exhibit both elastic and plastic anisotropy, which can alter the development of curvatures. Since peen forming relies on compressive stresses to upset equilibrium, resulting curvatures may also be affected by initial stresses in the part. In this work, the influence of the rolling direction orientation with respect to the sample was investigated experimentally and numerically for the first time for aluminium alloy 2024-T3 specimens. Although maximum deflections were only slightly dependent on the rolling direction orientation, it was found that radii of curvature varied by as much as 10% with respect to this parameter. Finite element simulations allowed quantification of the individual effects of non-equibiaxial initial stresses and elastic orthotropy. It was found that these factors can significantly influence curvature development. Comparison of experimental and numerical results suggested that plastic anisotropy should also be taken into account in future studies. The tools developed in this study show promises for the accurate prediction of peen forming process for large scale components.     

大厚度双曲度铝合金飞机蒙皮拉伸成形工艺优化

拉伸成形工艺是飞机蒙皮零件的基本成形方法。针对某大厚度双曲度铝合金飞机蒙皮进行了拉伸成形工艺研究和优化。为了保证数值模拟的准确性和可靠性,进行了材料性能测试试验,获取了该蒙皮多道次加工时每一道次、不同热处理状态下的材料性能。通过数值模拟,研究了拉伸成形工艺参数包括各道次拉伸量、上模压力、合模间距对贴模和回弹的影响规律。结果表明:合模间距为7 mm时,成形后零件的厚度在大部分区域基本均匀;上模压力在200~1000 kN之间时,增加压力能有效地改善贴模度。据此,提出了优化拉伸成形工艺。针对该蒙皮零件厚度大而导致的回弹大、仅靠工艺优化不能完全满足贴模度要求的问题,进行了模具型面补偿研究。结果表明,该工艺可用于生产满足质量要求的蒙皮零件,并能减少成形道次、降低加工成本、提高生产效率。     

局部凸柱面压料面对方盒形件成形的影响

压料面是工艺补充的一个重要组成部分,对汽车覆盖件的拉深成形起着重要作用.通过数值模拟的方法研究了局部凸柱面压料面形式对方盒形件拉深成形的影响,获得了局部凸柱面压料面形式对毛坯变形区应变分布影响的规律.结果表明:压料面形状在很大程度上决定了毛坯变形区的应力状态,通过控制压料面形状可以控制材料的变形流动,上凸压料面可以改善局部板平面内的压应力状态,减小起皱,提高成形性.     

喷丸残余应力对裂纹闭合效应影响的数值仿真

基于裂纹闭合效应,利用ABAQUS软件建立用于预测残余应力场中疲劳裂纹扩展特性的弹塑性有限元模型。考虑塑性和残余应力场对裂纹闭合的作用,分析残余应力、应力比和裂尖单元尺寸对裂纹闭合效应的影响。研究结果表明:未喷丸试样的裂纹闭合类型为塑性诱导裂纹闭合,喷丸残余应力场中的裂纹闭合为塑性和残余压应力共同作用,且裂纹张开力的大小与残余应力的分布相对应;正应力比越大,裂纹闭合效应越不明显,疲劳裂纹扩展速率越快;裂尖单元尺寸小于塑性区范围时可以真实反映裂尖的闭合状态;喷丸残余压应力通过提高裂纹闭合力,增强裂纹闭合效应,抑制疲劳裂纹扩展。     

整体壁板增量压弯过程应力应变模拟

整体壁板结构特点为蒙皮和纵横交错的加强筋为一整体,将机械加工后的平面外形的壁板毛坯成形为具有复杂曲面外形的壁板零件具有很大的难度。本文采用MARC有限元软件分析了整体壁板成形过程中应力应变变化情况。研究表明:整体壁板成形过程中,筋条处的应力状态最为恶劣,筋条与蒙皮过渡区处于三向拉应力状态,同时有剪切塑性应变发生,容易导致该处开裂,对于高筋条来说,还容易导致失稳现象发生;筋条的塑性变形既有凸模下压导致的塑性变形,又有蒙皮回弹导致的塑性变形;塑性变形区主要集中于筋部,蒙皮几乎不发生塑性变形;成形后的壁板将保留较大的残余应力,该应力主要是由蒙皮弹性回复所引起。