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《中国航空学报》2021,34(5):617-627
In this paper, a progressive approach to predict the multiple shot peening process parameters for complex integral panel is proposed. Firstly, the invariable parameters in the forming process including shot size, mass flow, peening distance and peening angle are determined according to the empirical and machine type. Then, the optimal value of air pressure for the whole shot peening is selected by the experimental data. Finally, the feeding speed for every shot peening path is predicted by regression equation. The integral panel part with thickness from 2 mm to 5 mm and curvature radius from 3200 mm to 16000 mm is taken as a research object, and four experiments are conducted. In order to design specimens for acquiring the forming data, one experiment is conducted to compare the curvature radius of the plate and stringer-structural specimens, which were peened along the middle of the two stringers. The most striking finding of this experiment is that the outer shape error range is below 3.9%, so the plate specimens can be used in predicting feeding speed of the integral panel. The second experiment is performed and results show that when the coverage reaches the limit of 80%, the minimum feeding speed is 50 mm/s. By this feeding speed, the forming curvature radius of the specimens with different thickness from the third experiment is measured and compared with the research object, and the optimal air pressure is 0.15 MPa. Then, the plate specimens with thickness from 2 mm to 5 mm are peened in the fourth experiment, and the measured curvature radius data are used to calculate the feeding speed of different shot peening path by regressive analysis method. The algorithm is validated by forming a test part and the average deviation is 0.496 mm. It is shown that the approach can realize the forming of the integral panel precisely. 相似文献
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为了进一步提高短舱内外流的气动性能,基于类别形状函数方法建立了曲率连续的非轴对称短舱气动型面参数化设计方法。主要思路是先设计关键截面型线,再设计纵向型线,最后通过纵向型线周向有序组合建立气动型面。为评价所建立的短舱气动型面设计方法的适用性,从曲率半径分布、主要工况下的流动特性和气动性能三个方面对所发展的方法和基于圆锥曲线的方法设计的超大涵道比(UHBPR)短舱进行了对比研究。结果表明:与基于圆锥曲线的方法设计的短舱相比,所建立的方法设计的短舱气动型面不存在轴向曲率半径波动。由于消除了曲率波动引起的短舱壁面附近局部过度加速形成的高速低压区,在马赫数为0.8的巡航条件下外罩壁面局部阻力降低了4.5%;在马赫数为0.82的飞行工况下,外罩壁面局部阻力降低了5.5%。进气道气动型面设计方法的改进,使得大攻角爬升条件下进气道总压恢复系数提高了0.41%,稳态周向总压畸变指数减小了8.82%。 相似文献
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《中国航空学报》2020,33(2):730-739
In order to ensure machining stability, curvature continuity and smooth cutting force are very important so as to meet the constraints of both cutting force and kinematics of machine tools. For five-axis flank milling, it is difficult to meet both of the constraints because tool path points and tool axis vectors interact with each other. In this paper, multiple relationships between tool path points and tool axis vectors with cutting force and kinematics of machine tools are established, and the strategies of corner-looping milling and clothoidal spirals are combined so as to find feasible solutions under both of the constraints. Tool path parameters are iterated by considering the maximum cutting force and the feasible range of the tool axis vector, and eventually a curvature continuity five-axis flank milling tool path with smooth cutting force is generated. Machining experimental results show that the conditions of cutting force are satisfied, vibration during the process of machining is reduced, and the machining quality of the surface is improved. 相似文献
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磁层磁场的几何结构是空间物理中的重要研究内容.本文采用曲率半径分析方法,结合Cluster立体探测的相关知识和背景,利用Cluster立体探测的优势,通过对Cluster 2001年的立体探测数据的研究,分析了磁层各区域的磁力线结构,包括背阳面、Cusp区以及昏侧,得出各区域中磁力线的曲率半径大小,曲率矢量以及磁力线密切面的法线矢量的方向.利用这些参量直接确定出该区域中磁力线的空间几何构型,进而揭示了该区域磁场的三维立体结构.所得结果也验证了曲率半径分析方法的正确性.在科学探测数据完备的情况下,将这一研究方法应用到磁层中其他所有区域,可以得到整个磁层的详细三维结构模型,这具有重要的科学意义. 相似文献
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This paper introduces a novel design method of highly loaded compressor blades with air injection.CFD methods were firstly validated with existing data and then used to develop and investigate the new method based on a compressor cascade.A compressor blade is designed with a curvature induced pressure-recovery concept.A rapid drop of the local curvature on the blade suction surface results in a sudden increase in the local pressure,which is referred to as a curvature induced ‘Shock'.An injection slot downstream from the ‘Shock' is used to prevent ‘Shock' induced separation,thus reducing the loss.As a result,the compressor blade achieves high loading with acceptable loss.First,the design concept based on a 2D compressor blade profile is introduced.Then,a 3D cascade model is investigated with uniform air injection along the span.The effects of the incidence are also investigated on emphasis in the current study.The mid-span flow field of the 3D injected cascade shows excellent agreement with the 2D designed flow field.For the highly loaded cascade without injection,the flow separates immediately downstream from the ‘Shock';the initial location of separation shows little change in a large incidence range.Thus air injection with the same injection configuration effectively removes the flow separation downstream from the curvature induced ‘Shock' and reduces the size of the separation zone at different incidences.Near the endwall,the flow within the incoming passage vortex mixes with the injected flow.As a result,the size of the passage vortex reduces significantly downstream from the injection slot.After air injection,the loss coefficient along spanwise reduces significantly and the flow turning angle increases. 相似文献
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为优化压气机叶片前缘形状以改善叶型性能,提出了一种曲率连续叶片前缘的设计方法。前缘设计过程基于三次Bezier曲线,只需引入三个设计变量。使用该方法对可控扩散叶型前缘进行了重新设计,并采用计算流体力学方法比较了不同前缘形状对于叶型气动性能的影响。计算结果表明新型前缘在来流马赫数0.2和0.6两种下均能够有效抑制前缘分离泡的产生和发展,与圆弧形和椭圆形前缘相比叶型攻角范围分别扩大约1.2°和2.5°。对跨声转子叶片的前缘进行重新设计后,提高了动叶效率,扩大了稳定工作范围。 相似文献