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2009 Vol. 52, No. 4
Published: 2009-02-15
FIGURE
FORUM
NEW VIEWPOINT
RESEARCH
COVER STORY
FIGURE
26
Automated Non-destructive Testing Techniques and Its Applications
DOI: 10.16080/j.issn1671-833x.2009.04.007
2009 Vol. 52 (4): 26-31 [
Abstract
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80
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COVER STORY
34
Applications of Robotics Technology in Aviation Industry
DOI: 10.16080/j.issn1671-833x.2009.04.023
2009 Vol. 52 (4): 34-39 [
Abstract
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85
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(1862 KB) (
1295
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FORUM
42
Laser Measurement for Gap Between Diffuser Vanes of Tandem Cascades
DOI: 10.16080/j.issn1671-833x.2009.04.013
2009 Vol. 52 (4): 42-46 [
Abstract
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76
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(812 KB) (
203
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47
Development of Metal Matrix Composite Ultrasonic Non-destructive Testing and Evaluation Techniques
DOI: 10.16080/j.issn1671-833x.2009.04.014
2009 Vol. 52 (4): 47-50 [
Abstract
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78
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(1021 KB) (
644
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54
Innovation of Eddy Current Image
DOI: 10.16080/j.issn1671-833x.2009.04.009
2009 Vol. 52 (4): 54-55 [
Abstract
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78
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(767 KB) (
221
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NEW VIEWPOINT
60
Brief Analysis on Key Manufacturing Technologies of Modern Aircraft
DOI: 10.16080/j.issn1671-833x.2009.04.016
2009 Vol. 52 (4): 60-63 [
Abstract
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80
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(987 KB) (
587
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64
Current Status of Large Aircraft Skin and Panel Manufacturing Technologies
DOI: 10.16080/j.issn1671-833x.2009.04.017
2009 Vol. 52 (4): 64-66 [
Abstract
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121
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(736 KB) (
928
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RESEARCH
70
Analysis of Composite Laminate Interference-Fit Linked With Interference Blind Bolt
DOI: 10.16080/j.issn1671-833x.2009.04.004
The dynamic three-dimensional finite element analysis on the assembly process of the interference blind bolt fastening system is simulated by ANSYS 11.0 software. The dynamic finite element model is developed by analyzing the characteristics of the joint, simplifying the construction of model, adopting “ pressure assembly ” method. According to the actual assembly process, the whole assembly process is simulated dynamically by imposing the displacement loads and boundary conditions. The stress plot of interference fit is acquired by running the program.
2009 Vol. 52 (4): 70-72/77 [
Abstract
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75
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(434 KB) (
207
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73
Matching Technology of Free ￣ Form Surface
DOI: 10.16080/j.issn1671-833x.2009.04.018
Error testing of free-form surface is discussed, and surface matching is studied in detail. First, center coordinate system of data points and free-form surface are defined by simplified method, and the pre-matching by using principal axes method is proposed, which can provide reliable initial matching result to avoid converging to local minimum of general methods. Then, accurate surface matching method based on iterative optimizing is presented, which can reduce the influence of local high distort points efficiently by modifying target function and selecting deviation bound. The results show the efficiency of this method.
2009 Vol. 52 (4): 73-77 [
Abstract
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83
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(450 KB) (
166
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78
Residual-Stress Distribution of High-Temperature Alloy GH3536 Welded by EBW
DOI: 10.16080/j.issn1671-833x.2009.04.005
A strip cutting method is used to determine the residual stresses distribution of GH3536 high-temperature alloy plates of 10mm in thickness welded by EBW. The results showed that the distribution of residual stress is about 4 to 7 times of the width of the welding seam and the maximum residual stress could be the yield limit. The results offer a theory basis for optimizing the technology of EBW and controlling residual stress and strain.
2009 Vol. 52 (4): 78-80 [
Abstract
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68
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162
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81
Construction and Application of Knowledge Template for Turbine Blade Mould
DOI: 10.16080/j.issn1671-833x.2009.04.019
For the purpose of shortening design time of the investment casting mould for turbine blade, the construction and design method of product knowledge template are studied, and a new rapid design method based on knowledge template is presented. Based upon mining and summarizing the design knowledge and parameter rules, the knowledge template of outside structure of turbine blade mould is constructed. The experiment shows that the design based on knowledge template is effective and practical.
2009 Vol. 52 (4): 81-85/89 [
Abstract
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78
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(599 KB) (
398
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86
Low-Scattering Pylon Structure Used in Stealth Property Measurement of Aircraft and Its Manufacture Technology
DOI: 10.16080/j.issn1671-833x.2009.04.020
Based on the structure characte-ristics and basic performance requirements of target support pylon, general manufacture technology process is presented. The concrete measure of target support pylon manufacture technology and whole craft course are discussed in detail and the basic law of improving performance is analyzed.
2009 Vol. 52 (4): 86-89 [
Abstract
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67
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258
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90
Reliability Design Principle of LVDT in Aircraft Braking System
DOI: 10.16080/j.issn1671-833x.2009.04.010
The reliability design principle of LVDT in the aircraft braking system is introduced. The reliability index that aircraft braking system distributes to dictating sensor is analyzed. By means of adding reliability index into LVDT design, the reliability design of product is realized. A series of reliability tests show that reliability design of LVDT is right, practical and feasible.
2009 Vol. 52 (4): 90-93 [
Abstract
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70
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(305 KB) (
379
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