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| Non-destructive Measurement of Internal Stress of Aircraft Aluminum Alloy Assembly Simulation Part for Stress Corrosion Test |
| Received:March 12, 2021 Revised:May 11, 2021 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2021.11.014 |
| KeyWord:assembly stress high-strength aluminum alloy internal stress bolt connection short-wavelength characteristic X-ray diffraction non-destructive testing stress corrosion cracking fatigue |
| Author | Institution |
| ZHENG Lin |
Southwest Institute of Technology and Engineering, Chongqing , China;National Defense Science and Technology Industry Natural Environment Experimental Research Center, Chongqing , China |
| DOU Shi-tao |
Southwest Institute of Technology and Engineering, Chongqing , China;National Defense Science and Technology Industry Natural Environment Experimental Research Center, Chongqing , China;Institute of Advanced Materials Technology, University of Science and Technology Beijing, Beijing , China |
| LI Wei |
Shenyang Aircraft Design Institute, Shenyang , China |
| ZHANG Jin |
Institute of Advanced Materials Technology, University of Science and Technology Beijing, Beijing , China |
| XU Wei-sheng |
Institute of Advanced Materials Technology, University of Science and Technology Beijing, Beijing , China |
| CHEN Xin |
Southwest Institute of Technology and Engineering, Chongqing , China;National Defense Science and Technology Industry Natural Environment Experimental Research Center, Chongqing , China |
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| Abstract: |
| To reduce or avoid stress corrosion and corrosion fatigue cracking of the aircraft body in service, short-wavelength characteristic X-ray diffraction technology and equipment were used to non-destructively detect the distribution of internal residual stress and assembly stress of aircraft aluminum alloy assembly simulation parts. The 0.5 mm rectangular gap caused a tensile stress of 110 MPa and above on the upper surface of the root of lower edge of the strip parts; the 0.3 mm rectangular gap caused a tensile stress of about 80 MPa on the upper surface of the root of lower edge of the strip parts; the 0.5 mm wedge-shaped gap caused an average tensile stress of about 55 MPa on the upper surface of the root of lower edge of the strip parts. By short-wavelength characteristic X-ray diffraction technology, the internal stress of aluminum alloy components and the distribution of it are non-destructively measured and characterized. The assembly gap caused large tensile stress on the upper surface layer of the lower edge of the strip parts, which is consistent with the position where there are more atypical cracks in the screwed parts of the aircraft fuselage in service; the tensile stress of the upper surface layer of the lower edge of the strip parts of the rectangular gap assembly is greater than that of wedge-shaped assembly parts with the same gap value, and the smaller the assembly gap, the smaller the tensile stress. Reducing the ratio of the assembly gap at the root of the nut to the distance from the root of the nut to the wall plate will decrease the tensile stress of the assembly parts, reduce or avoid the occurrence of SCC&CFC and the occurrence of atypical cracks. |
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