13 Study on Bearing Mechanism of Composite Stiffened Panel …
171
damage, and mainly distributed in the position where the lower flange is far
away from the loading point.
(b) The main reason of different size of embedded delamination on the damage
propagation of skin and stringer is limited is that the performance of the adhesive
film is relatively low, and the debonding of the skin and the stringer occurs
prematurely before the damage occurs, which reduces the load transferred to
the stringer.
References
1. Degenhardt, R., Rolfes, R., Zimmermann, R., Rohwer, K.: COCOMAT—improved material exploitation of composite airframe structures by accurate simulation of postbuckling and
collapse. Compos. Struct. 73(2), 175–178 (2006)
2. Zimmermann, R., Rolfes, R.: POSICOSS—improved postbuckling simulation for design of
fibre composite stiffened fuselage structures. Compos. Struct. 73(2), 171–174 (2006)
3. Mcelroy, M.: Use of an enriched shell finite element to simulate delamination-migration in a
composite laminate. Compos. Struct. 167, 88–95 (2017)
4. Park, H., Kong, C.: Experimental study on barely visible impact damage andvisible impact
damage for repair of small aircraft composite structure. Aerosp. Sci. Technol. 29, 363–372
(2013)
5. Al-Azzawi, A.S.M., McCrory, J., Kawashita, L.F., Featherston, C.A., Pullin, R., Holford, K.M.:
Buckling and postbuckling behaviour of Glare laminates containing splices and doublers. Part
1: Instrumented tests. Compos. Struct. 176, 1158–1169 (2017)
6. Al-Azzawi, A.S.M., Kawashita, L.F., Featherston, C.A.: Buckling and postbuckling behaviour
of Glare laminates containing splices and doublers. Part 2: Numerical modelling. Compos.
Struct. 176, 1170–1187 (2017)
7. Feng, Y., Zhang, H., Tan, X., He, Y., An, T., Zheng, J.: Effect of impact damage positions on
the buckling and post-buckling behaviors of stiffened composite panel. Compos. Struct. 155,
184–196 (2016)
8. Feng, Y., He, Y., Tan, X., An, T., Zheng, J.: Experimental investigation on different positional
impact damages and shear-after-impact (SAI) behaviors of stiffened composite panels. Compos.
Struct. 178, 232–245 (2017)
9. Feng, Y., He, Y., Zhang, H., Tan, X., An, T., Zheng, J.: Effect of fatigue loading on impact
damage and buckling/post-buckling behaviors of stiffened composite panels under axial
compression. Compos. Struct. 164, 248–262 (2017)
10. Feng, Y., He, Y., Tan, X., An, T., Zheng, J.: Investigation on impact damage evolution under
fatigue load and shear-after-impact- fatigue (SAIF) behaviors of stiffened composite panels.
Int. J. Fatigue 100, 308–321 (2017)
11. Sun, W., Guan, Z., Ouyang, T., Tan, R., Zhong, X.: Effect of stiffener damage caused by low
velocity impact on compressive buckling and failure modes of T-stiffened composite panels.
Compos. Struct. 184, 198–210 (2018)
12. Sun, W., Guan, Z., Li, Z., Ouyang, T., Jiang, Y.: Modelling and simulating of the compressive
behavior of T-stiffened composite panels subjected to stiffener impact. Compos. Struct. 186,
221–232 (2018)
13. Li, N., Chen, P.: Experimental investigation on edge impact damage and Compression-AfterImpact (CAI) behavior of stiffened composite panels. Compos. Struct. 138, 134–150 (2016)
14. Boni, L., Fanteria, D., Lanciotti, A.: Post-buckling behaviour of flat stiffened composite panels:
Experiments vs. analysis. Compos. Struct. 94(12), 3421–3433 (2012)
171
damage, and mainly distributed in the position where the lower flange is far
away from the loading point.
(b) The main reason of different size of embedded delamination on the damage
propagation of skin and stringer is limited is that the performance of the adhesive
film is relatively low, and the debonding of the skin and the stringer occurs
prematurely before the damage occurs, which reduces the load transferred to
the stringer.
References
1. Degenhardt, R., Rolfes, R., Zimmermann, R., Rohwer, K.: COCOMAT—improved material exploitation of composite airframe structures by accurate simulation of postbuckling and
collapse. Compos. Struct. 73(2), 175–178 (2006)
2. Zimmermann, R., Rolfes, R.: POSICOSS—improved postbuckling simulation for design of
fibre composite stiffened fuselage structures. Compos. Struct. 73(2), 171–174 (2006)
3. Mcelroy, M.: Use of an enriched shell finite element to simulate delamination-migration in a
composite laminate. Compos. Struct. 167, 88–95 (2017)
4. Park, H., Kong, C.: Experimental study on barely visible impact damage andvisible impact
damage for repair of small aircraft composite structure. Aerosp. Sci. Technol. 29, 363–372
(2013)
5. Al-Azzawi, A.S.M., McCrory, J., Kawashita, L.F., Featherston, C.A., Pullin, R., Holford, K.M.:
Buckling and postbuckling behaviour of Glare laminates containing splices and doublers. Part
1: Instrumented tests. Compos. Struct. 176, 1158–1169 (2017)
6. Al-Azzawi, A.S.M., Kawashita, L.F., Featherston, C.A.: Buckling and postbuckling behaviour
of Glare laminates containing splices and doublers. Part 2: Numerical modelling. Compos.
Struct. 176, 1170–1187 (2017)
7. Feng, Y., Zhang, H., Tan, X., He, Y., An, T., Zheng, J.: Effect of impact damage positions on
the buckling and post-buckling behaviors of stiffened composite panel. Compos. Struct. 155,
184–196 (2016)
8. Feng, Y., He, Y., Tan, X., An, T., Zheng, J.: Experimental investigation on different positional
impact damages and shear-after-impact (SAI) behaviors of stiffened composite panels. Compos.
Struct. 178, 232–245 (2017)
9. Feng, Y., He, Y., Zhang, H., Tan, X., An, T., Zheng, J.: Effect of fatigue loading on impact
damage and buckling/post-buckling behaviors of stiffened composite panels under axial
compression. Compos. Struct. 164, 248–262 (2017)
10. Feng, Y., He, Y., Tan, X., An, T., Zheng, J.: Investigation on impact damage evolution under
fatigue load and shear-after-impact- fatigue (SAIF) behaviors of stiffened composite panels.
Int. J. Fatigue 100, 308–321 (2017)
11. Sun, W., Guan, Z., Ouyang, T., Tan, R., Zhong, X.: Effect of stiffener damage caused by low
velocity impact on compressive buckling and failure modes of T-stiffened composite panels.
Compos. Struct. 184, 198–210 (2018)
12. Sun, W., Guan, Z., Li, Z., Ouyang, T., Jiang, Y.: Modelling and simulating of the compressive
behavior of T-stiffened composite panels subjected to stiffener impact. Compos. Struct. 186,
221–232 (2018)
13. Li, N., Chen, P.: Experimental investigation on edge impact damage and Compression-AfterImpact (CAI) behavior of stiffened composite panels. Compos. Struct. 138, 134–150 (2016)
14. Boni, L., Fanteria, D., Lanciotti, A.: Post-buckling behaviour of flat stiffened composite panels:
Experiments vs. analysis. Compos. Struct. 94(12), 3421–3433 (2012)