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| Identification of Aircraft Skin Distributed Dynamic Load Based on Strain Modal Method |
| Received:July 09, 2020 Revised:July 13, 2020 |
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| DOI：10.7643/issn.1672-9242.2020.09.020 |
| KeyWord:strain modal load identification structural dynamics orthogonal polynomial |
| Author | Institution |
| ZHANG Cong |
Hanzhong Branch of AVIC Aircraft Co., Ltd, Hanzhong , China |
| FU Yi-zhan |
Hanzhong Branch of AVIC Aircraft Co., Ltd, Hanzhong , China |
| LI Yuan-dong |
Hanzhong Branch of AVIC Aircraft Co., Ltd, Hanzhong , China |
| LI Jia-xu |
Hanzhong Branch of AVIC Aircraft Co., Ltd, Hanzhong , China |
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| Abstract: |
| To solve the practical engineering problem of distributed dynamic load identification on aircraft skin, this paper combined the strain modal theory and the complex distributed dynamic load identification technology based on the generalized orthogonal polynomials, established a distributed dynamic load identification model of aircraft skin with the structural strain response of limited measuring points and strain transfer function as the known parameters. Taking the outer skin of a certain aircraft fuselage as an example, the distributed dynamic load identification of skin was carried out at 70, 80, 90 and 100 Hz by both displacement mode method and strain mode method with NASTRAN software, and a comparative analysis was carried out. The example showed that the method of dynamic load identification of aircraft skin distribution using strain mode method had good accuracy of load identification and the maximum identification error was 8.9%, which can meet the needs of engineering application. The condition number of integral matrix based on strain modal method was lower than those based on displacement method at each frequency. The maximum identification error of displacement method reached 19.4% when 3% random noise was applied, while the identification error of the maximum strain method was 9.8%. Compared with the traditional method of load identification using displacement mode, the strain modal load identification method with strain response as a known parameter has better numerical stability, which has a good application value for solving the singularity problem of frequency response function matrix near the resonance frequency of structure. |
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