[1] Federal Aviation Administration, Department of Transportation. AC20-107B Subject:Composite aircraft structure, advisory circular[S]. Washington D.C.:Federal Aviation Administration, Department of Transportation, 2009:12-14.
[2] 矫桂琼,杜凯,杨成鹏,等.含离散源损伤复合材料加筋板的压缩特性[J]. 航空学报,2007, 28(6):1383-1388. JIAO G Q, DU K, YANG C P, et al. Compressive properties of stiffened composite panels with discrete-source damage[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(6):1383-1388(in Chinese).
[3] 杜凯, 矫桂琼,王翔.含离散源损伤复合材料加筋板的拉伸特性[J]. 复合材料学报,2008, 25(4):181-186. DU K, JIAO G Q, WANG X. Tensile properties of stiffened composite panels with discrete-source damage[J]. Acta Materiae Compositae Sinica, 2008, 25(4):181-186(in Chinese).
[4] WALKER T H, MINGUET P J, FLYNN B W, et al. Advanced technology composite fuselage-structure performance:NASA CR-4732[R]. Washington, D.C.:NASA,1997.
[5] WANG J, LOTTS C, SLEIGHT D. Analysis of discrete-source damage progression in a tensile stiffened composite panel[C]//40th Structures, Structural Dynamics, and Materials Conference and Exhibit, 1999.
[6] ALEX V. Designing primary structures with stitched composites[C]//31 st Congress of the International Council of the Aeronautical Sciences, 2018.
[7] ANDREW B, JOHN G B J, ANDREW L, et al. Full-scale test and analysis results of a PRSEUS fuselage panel to assess damage containment features[C]//Aircraft Airworthiness & Sustainment Conference, 2012.
[8] XU X D, TAKEDA S I, AOKI Y, et al. Predicting notched tensile strength of full-scale composite structures from small coupons using fracture mechanics[J]. Composite Structures, 2017, 180:386-394.
[9] WANG J T, POE C C, AMBUR D R, et al. Residual strength prediction of damaged composite fuselage panel with R-curve method[J]. Composites Science and Technology, 2006, 66(14):2557-2565.
[10] LIANG L, JIA P R, JIAO G Q. Progressive failure study of discrete-source damage in stiffened composite panels[J]. Advanced Materials Research, 2011, 314-316:963-967.
[11] 李亮. 含离散源损伤复合材料结构失效行为研究[D]. 西安:西北工业大学, 2016:123-148. LI L. Failure behavior investigation of the composite structures with discrete resource damage[D]. Xi'an:Northwestern Polytechnical University, 2016:123-148(in Chinese).
[12] 李航,矫桂琼,王波. 含离散源损伤Z向增强复合材料加筋板压缩特性研究[J]. 机械强度,2012, 34(1):37-42. LI H,JIAO G Q,WANG B. Study on compressive properties of z-reinforced stiffened composite plate with discrete-source damage[J]. Journal of Mechanical Strength, 2012, 34(1):37-42(in Chinese).
[13] 李航,矫桂琼,赵龙,等. 含切口复合材料加筋板的压缩剩余强度研究[J]. 工程力学,2011, 28(8):133-137. LI H,JIAO G Q,ZHAO L, et al. Progressive failure analysis of stiffened composite plate with notch[J]. Engineering Mechanics, 2011, 28(8):133-137(in Chinese).
[14] 陈向明,张阿盈,柴亚南,等. 复合材料机翼壁板离散源损伤修理评估方法[J]. 机械强度,2017, 39(2):457-462. CHEN X M, ZHANG A Y, CHAI Y N, et al. Assessment method of the repaired aircraft composite wing panel with discrete-source damage[J]. Journal of Mechanical Strength,2017, 39(2):457-462(in Chinese).
[15] 陈向明,张阿盈,柴亚南,等. 复合材料机翼壁板离散源损伤修理技术研究[J]. 机械强度,2017, 39(3):551-556. CHEN X M, ZHANG A Y, CHAI Y N, et al. Investigation of repair technique for aircraft composite wing panel with discrete-source damage[J]. Journal of Mechanical Strength,2017,39(3):551-556(in Chinese).
[16] 陈向明,张阿盈,王力立,等. 复合材料加筋壁板修理后压缩性能试验研究[J]. 工程与试验,2017,57(1):9-13. CHEN X M, ZHANG A Y,WANG L L, et al. Experimental research on compression performance of repaired composite stiffened panel[J]. Engineering & Test, 2017, 57(1):9-13(in Chinese).
[17] 张阿盈,陈向明,王力立. 含离散源损伤复合材料加筋板剩余强度及其修理技术研究[J]. 工程与试验,2018,58(2):16-19. ZHANG A Y,CHEN X M, WANG L L. Study on residual strength of composite stiffened panel with discrete source damage and repair technique[J]. Engineering & Test, 2018,58(2):16-19(in Chinese).
[18] WHITNEY J M, NUISMER R J. Stress fracture criteria for laminated composites containing stress concentrations[J]. Journal of Composite Materials, 1974, 8(3):253-265.
[19] NUISMER R, WHITNEY J. Uniaxial failure of composite laminates containing stress concentrations[J]. Fracture Mechanics of composites, 1975, 9:117-142.
[20] VAIDYA R S, SUN C T. Fracture criterion for notched thin composite laminates[J]. AIAA Journal, 1997, 35(2):311-316.
[21] CHEN P H,SHEN Z,WANG J Y. A new method for compression after impact strength prediction of composite laminates[J]. Journal of Composite Materials, 2002, 36(5):589-610.
[22] 中国航空研究院. 复合材料结构设计手册[M]. 北京:航空工业出版社,2001:365-390. Institute of Aeronautics China. Handbook of composites structure design[M]. Beijing:Aviation Industry Press, 2001:365-390(in Chinese).
[23] 李仲,葛森,杨胜春,等. 含损伤缝合复合材料层压板压缩剩余强度估算方法[J]. 西北工业大学学报,2007,25(3):342-346. LI Z, GE S, YANG S C, et al. Prediction of compressive residual strength for stitched composite laminates with damage[J]. Journal of Northwestern Polytechnical University, 2007,25(3):342-346(in Chinese).
[24] 汪厚冰,李新祥,魏景超,等. 复合材料曲面帽形加筋壁板在内压-轴压联合载荷下的屈曲及承载性能[J]. 航空制造技术,2020,63(18):55-64. WANG H B, LI X X, WEI J C, et al. Buckling and post-buckling of curved hat-stiffened composite panels under combined internal pressure and axial compression[J]. Aeronautical Manufacturing Technology, 2020,63(18):55-64(in Chinese).
[25] 魏宏艳. 应力集中方法试验:AA-623S-2018-101-0025[R]. 西安:中国飞机强度研究所技术报告,2018. WEI H Y. Supplementary test report of stress concentration:AA-623S-2018-101-0025[R].Xi'an:Aircraft strength Research Institute of China, 2018(in Chinese).
[26] 邓凡臣. 应力集中方法补充试验报告:43-623S-2020-101-0015[R]. 西安:中国飞机强度研究所技术报告,2018. DENG F C. Test report of stress concentration, ASRI,43-623S-2020-101-0015[R]. Xi'an:Aircraft strength Research Institute of China, 2020(in Chinese).
[27] 汪厚冰,陈昊,雷安民,等. 复合材料帽形加筋壁板轴压屈曲与后屈曲性能[J]. 复合材料学报,2018,35(8):2014-2022. WANG H B,CHEN H,LEI A M,et al. Buckling and post-buckling performance of hat-stiffened composite panels under axial compression load[J]. Acta Materiae Compositae Sinica, 2018,35(8):2014-2022(in Chinese).
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