Chengdu Aircraft Industrial Co.

www.cac.com.cn
Chengdu, China

The Chengdu Aircraft Industry Group or Chengdu Aerospace Corporation, a subsidiary of AVIC, is a Chinese aerospace conglomerate that manufactures aircraft parts as well as designs and manufactures combat aircraft. It was founded in 1958 in Chengdu, Sichuan province, China to be a supplier of aircraft for the Chinese military.The Chengdu Aerospace Corporation designed and now produces the Chengdu J-10B medium-weight multi-role fighter that is considered to be one of the most advanced in China's inventory, as well as the FC-1 / JF-17 light-weight multi-role fighter that is produced in cooperation with Pakistan. Wikipedia.

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Han X.,Chengdu Aircraft Industrial Co. | Tang L.,Chengdu Aircraft Industrial Co.
International Journal of Machine Tools and Manufacture | Year: 2015

Pocket corner is the most typical characters of aerospace structure components. To achieve high-quality product and stable machining operation, manufacturer constantly seek to control the cutting forces in pocket corner milling process. This paper presents the cutting force in corner milling considering the precision instantaneous achievements of tool engagement angle and undeformed chip thickness. To achieve the actual milling tool engagement angle in corner milling process, the details of tool-corner engagement relationship are analyzed considering the elements of tool trajectory, tool radius, and corner radius. The actual undeformed chip thicknesses in up and down milling operations are approached on account of the trochoid paths of adjacent teeth by a presented iteration algorithm. Error analysis shows that the presented models of tool engagement angle and undeformed chip thickness have higher precision comparing with the traditional models. Combined with the cutting force coefficients fitted by a series of slot milling tests, the predicted cutting force in milling titanium pocket with different corner structure and milling parameters are achieved, and the prediction accuracy of the model was validated experimentally and the obtained predict and the experiment results were found in good agreement. © 2014 Elsevier Ltd. All rights reserved.


Huang R.,Chengdu Aircraft Industrial Co.
Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics | Year: 2010

The default pressure control algorithm for commercial software MARC is improved. The improved algorithm can limit the deformation rate based on the average strain rate of the elements with the 20 highest strain rates in superplastic forming. Pressure cycles are obtained and the finite element analysis is performed for a complex TC4 box-shaped part. The complex TC4 box-shaped parts are manufactured. The predicted profile is in agreement with that of the strain rate control algorithm and the measured thickness distribution. Thus, the better thickness distribution uniformity of the formed part is improved on the modified pressure cycle.


Li H.,Northwestern Polytechnical University | Yang H.,Northwestern Polytechnical University | Song F.F.,Northwestern Polytechnical University | Zhan M.,Northwestern Polytechnical University | Li G.J.,Chengdu Aircraft Industrial Co.
Journal of Materials Processing Technology | Year: 2012

Stress-relieved Ti-3Al-2.5V bent tube in hydraulic bleeding systems improves the overall performance of advanced aircraft and spacecraft due to its unique high specific strength. However, the high ratio of yield strength to Young's modulus may induce significant elastic recovery after unloading. The precision bending of the high strength Ti-tube (HSTT) depends on the understanding of the springback features and mechanisms. Using the plasticity deformation theory, the explicit/implicit 3D-FE and the physical experiments, the springback behaviors of the HSTT under multi-die constrained cold rotary draw bending (RDB) are addressed. The results show that: 1) The elastic recovery of the HSTT should be characterized by the significant angular springback, the radius growth and the sectional springback; Both the angular and radius springback should be compensated, while the sectional one decreases the cross-section flattening; 2) Among multiple parameters, both the material properties (Young's modulus, strength coefficient and anisotropy exponent) and the geometrical dimensions (bending angle and bending radius) dominate the unloading; Both the angular and radius springback values decrease with the smaller bending radii; The angular springback increases linearly with the larger bending angles, while the radius growth fluctuates little with the increasing of the bending angles at the later bending stages; Both the springback values of the HSTT are far larger than the ones of the 5052O Al-alloy tube and the 1Cr18Ni9Ti tube; The maximum variations of the angular and radius springback with changing of the processing parameters are 78% and 62.5% less than the maximum ones under different material properties and geometrical ones, respectively. 3) A two level springback compensation methodology is proposed to achieve the precision bending in terms of both springback angle and radius. © 2012 Elsevier B.V. All rights reserved.


Li H.,Northwestern Polytechnical University | Yang H.,Northwestern Polytechnical University | Zhang Z.Y.,Northwestern Polytechnical University | Li G.J.,Chengdu Aircraft Industrial Co. | And 2 more authors.
Journal of Materials Processing Technology | Year: 2014

Understanding the bending limits is critical to extract the forming potential and to achieve precision tube bending. The most challenging task is the development of the tube bending limits in the presence of unequal deformation induced multiple instabilities and multi-factor coupling effects. Using analytical and 3D-FE methods as well as experiments, a comprehensive map of the tube bending limits during rotary draw bending is provided under a wide range of tube sizes, material types and processing parameters. The major results show: (1) For each instability, the intrinsic factors (tube geometrical parameters, D and t, and mechanical properties, m) dependent bending limits are clarified, and evident interactive or even conflicting effects are observed. (2) Under mandrel bending, the significant effects of the intrinsic factors on the wrinkling limit are reduced, the neglected effects of D/t on the thinning limit are magnified; the significant influences of D/t on the flattening limit even become contrary, and the effects of m on wrinkling and thinning limit are opposite to that on the flattening limit. (3) Taking D/t as the basic design parameter, a conceptual multiple defect-constrained bending limit diagram (BLD) is constructed, and a knowledge-based stepwise method for determining and improving tube bending limits is proposed, considering coupling effects of multiple forming parameters, e.g., intrinsic factors, tooling/processing parameters and uncertainties. (4) The method is experimentally verified by several practical bending scenarios for different kinds of tubular materials with extreme size. © 2013 Elsevier B.V.


Liu J.,Beihang University | Zhang D.,Beihang University | Qin L.,Chengdu Aircraft Industrial Co. | Yan L.,Beihang University
International Journal of Machine Tools and Manufacture | Year: 2012

Carbon fiber reinforced plastics (CFRP) are used for various aircraft structural components because of their superior mechanical and physical properties such as high specific strength, high specific stiffness, etc. However, when CFRP are machined, rapid tool wear and delamination are troublesome. Therefore, cost effective and excellent quality machining of CFRP remains a challenge. In this paper, the rotary ultrasonic elliptical machining (RUEM) using core drill is proposed for drilling of holes on CFRP panels. This method combines advantages of core-drill and elliptical tool vibration towards achieving better quality, delamination free holes. The cutting force model and chip-removal phenomenon in ultrasonic elliptical vibration cutting are introduced and analyzed. The feasibility to machine CFRP for RUEM is verified experimentally. The results demonstrate that compared to conventional drilling (CD), the chip-removal rate has been improved, tool wear is reduced, precision and surface quality around holes is enhanced, delamination at hole exits has been prevented and significant reduction in cutting force has been achieved. © 2011 Elsevier Ltd All rights reserved.


Jiang Z.Q.,Northwestern Polytechnical University | Yang H.,Northwestern Polytechnical University | Zhan M.,Northwestern Polytechnical University | Xu X.D.,Chengdu Aircraft Industrial Co. | Li G.J.,Chengdu Aircraft Industrial Co.
Materials and Design | Year: 2010

The significant springback after the numerically controlled (NC) bending of a titanium alloy tube has an important influence on the precision of the shape and size of the bent tube. This springback depends on the material properties of the tube, the bending angle, and especially their coupling effects. The influence of some material properties and the bending angle on the springback angle in the NC bending of a TA18 tube were investigated using a three-dimensional (3D) elastic-plastic finite element model. Using multivariate and stepwise analyses, the coupling effects of the bending angle and the material properties on the springback angle during NC bending were revealed. It was observed that Young's modulus, yield stress, the strain hardening coefficient and exponent, and the thickness anisotropy exponent, as well as interactions of these parameters with the bending angle, have a significant influence on the springback angle. The bending angle, yield stress, and hardening coefficient have positive effects on the springback angle, and Young's modulus, the hardening exponent, and the thickness anisotropy exponent have negative effects. The influence of the material properties of the titanium alloy increases with the bending angle. Young's modulus and the strain hardening coefficient and exponent have the greatest influence on the springback angle. The results will be very useful in predicting, compensating for and controlling the springback of titanium alloy tubes during NC bending. © 2009 Elsevier Ltd. All rights reserved.


Li Y.G.,Nanjing University of Aeronautics and Astronautics | Ding Y.F.,Nanjing University of Aeronautics and Astronautics | Mou W.P.,Chengdu Aircraft Industrial Co. | Guo H.,Changzhou Institute of Technology
Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture | Year: 2010

A feature-recognition method based on an holistic attribute adjacency graph is put forward to solve the problems that complex features of aircraft structural parts find difficult to recognize by traditional feature-recognition methods. Extending the attribute's information and adding node types based on a traditional attribute adjacency graph, the method not only represents freeform surfaces and edge features, but also describes geometric information of topology elements precisely and completely. Combining feature recognition based on a graph with that based on hint, the method can deal with feature recognition of freeform surfaces, edge features, intersecting features, and convex features by a uniform algorithm, which virtually performs hint search, hint extension, and feature combination with hints of seed faces. According to the research, an original system has been used in a numerically controlled machining process of integer frame parts in certain large aviation enterprises.


Chang N.,Northwestern Polytechnical University | Wang W.,Northwestern Polytechnical University | Yang W.,Chengdu Aircraft Industrial Co. | Wang J.,Queen's University of Belfast
Structural and Multidisciplinary Optimization | Year: 2010

Stacking sequence optimization (SSO) of laminate will greatly improve its mechanical properties without weight penalty. In this paper, a novel permutation discrete particle swarm optimization (PDPSO) method was proposed to perform SSO. To improve the efficiency of the algorithm, the concepts and techniques of valid/invalid exchange, checking memory and Self-escape were introduced into the PDPSO. In total 11 examples were presented. First, eight examples were carried out by employing the proposed method. The results show that the computational efficiency of PDPSO is greatly improved compared with standard discrete particle swarm optimization (SDPSO), and is comparable with that of gene rank crossover (GR) and partially mapped crossover (PMX). Then, three extra examples were presented, in which the outermost plies in the optimum design are not ±45° plies. The results show that the PDPSO has better stability and potential which demonstrate the better performance of PDPSO for laminates. Copyright © 2009 Springer-Verlag.


Sun Y.,Shandong University | Sun J.,Shandong University | Li J.,Shandong University | Xiong Q.,Chengdu Aircraft Industrial Co.
International Journal of Advanced Manufacturing Technology | Year: 2014

An investigation was reported on the cutting temperature in milling Ti6Al4V by applying semi-artificial thermocouple. ANOVA was conducted on the experimental results, and regression models were obtained. Analysis results showed that the tool temperature and workpiece temperature performed a similar rising trend with the increase of cutting parameters, including cutting speed, feed rate, radial feed, and axial feed. And their influence degrees decreased successively. The cutting force with different cutting parameters was also measured, and the relationship between cutting temperature and cutting force was discussed. It was found that cutting temperature and cutting force obtained in the experiment had the same fluctuation feature. Therefore, the cutting force and cutting temperature could complement each other for monitoring and analysis of the cutting process. © 2013 Springer-Verlag London.


Trademark
Chengdu Aircraft Industrial Co. | Date: 2016-09-19

Land vehicles; ships; water vehicles, namely, hydrofoil boats supported by single or multi hulls, and structural parts therefor; light rail vehicles; railway cars; aeroplanes; aircraft; aerial conveyors; boats; cable cars; unmanned aerial vehicles (UAVs).

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