大型民用飞机缝翼全尺寸静力试验载荷设计

doi:10.7527/S1000-6893.2018.22197

Abstract

Abstract: To examine the safety of the slat structure on large civil aircraft and verify the feasibility of its strength analysis, load design techniques for full scale static test are studied. To address the characteristics of slats such as small size, large curvature and complex load conditions, methods of baseline loads screening, test loads transfer and optimization are proposed, creating a set of load design processes that meet the requirements of airworthiness. Based on the principle of minimum margin of safety, baseline loads were selected. Aerodynamic distribution loads were converted into concentrated loads by setting up local coordinate system. Oblique loads were used to accurately simulate load conditions of slat under large deformation of the wing. The results of comparative analysis with theoretical loads showed the validity of the test load.Test results showed that load design techniques in this paper can be used for the verification of the airworthiness of slat's strength successfully.

Key words: civil aircraft, leading edge slat, verification of airworthiness, static test, load

CLC Number:

V216.1

HE Zhiquan, LIU Yang, LI Zejiang. Load design for full scale static test of slat on large civil aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(2): 522197-522197.

References

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Load design for full scale static test of slat on large civil aircraft

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