ACTA AERONAUTICAET ASTRONAUTICA SINICA >
A calculation method for load transfer in bolted repair of composite laminates based on spring-mass model
Received date: 2016-06-07
Revised date: 2016-07-15
Online published: 2016-08-15
Supported by
National Natural Science Foundation of China (U1233202)
Composite bolted repair provides the advantages of easy operation, fast processing and reliable performance, making it a preferable repair method for damaged composite structure, especially for battle damage repair. However, the repair design process is complex, and it is difficult to meet the need for rapid determination of parameters. In this paper, a simple method for estimate the load transfer in composite bolted repair is proposed based on the spring-mass model. The skin and the patch are first assumed to be of the same width. The model is then modified and applied to the bolted repair joint where the width of the skin is larger than that of the patch by introducing the principle of load transfer in materials according to their stiffness. The calculation method for equivalent stiffness of the damaged skin is discussed integrating the micromechanical method and the homogenization method. The calculation method for the equivalent bolt stiffness is given and proven to meet the principle of superposition for regular arrangement of bolts. The proposed method is validated by applying it to analyze the repair of damaged composite skin plate with a circular hole. The method is also compared with the finite element method (FEM). The results show that the predicted results by the proposed method agree well with those by the FEM, with the maximum error being 7.7%. The model could be used for efficient and accurate design and analysis of composite bolted repair joint.
Key words： composites; bolted repair; load transfer; bolt load distribution; spring-mass model
XIE Zonghong , LI Xiang , YANG Linya , WU Shi . A calculation method for load transfer in bolted repair of composite laminates based on spring-mass model[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(12) : 3742 -3751 . DOI: 10.7527/S1000-6893.2016.0211
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