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Optimized distortion control method of CFRP curing region temperature field driven by near⁃zero stress equivalent temperature field
Received date: 2023-10-11
Revised date: 2023-11-28
Accepted date: 2023-12-08
Online published: 2023-12-21
Supported by
National Natural Science Foundation of China(52175466)
The cure-induced distortion of Carbon Fiber Resin Matrix Composite （CFRP） components directly affects the mechanical properties and service life of the components after assembly. However， the cure-induced distortion control methods such as tool compensation and structure optimization have the problems of long process cycle time and high cost of iteration. Selective heating methods， such as microwave heating and self-resistive heating， have the potential to realize precise control of the curing temperature field， and generate thermal stresses to hedge the original cure-induced distortion by constructing an uneven temperature field. In this paper， the typical inverse problem of how to construct an inhomogeneous temperature field， a quasi “zero-stress” equivalent temperature field is derived and defined， which in principle can hedge the residual stress field of the component before demolding to achieve a quasi “zero-stress” curing， and thus inhibit the curing deformation after demolding. An adaptive compression partitioning algorithm is designed to partition the theoretical equivalent temperature field with respect to the actual curing temperature process constraints. The method is preliminarily validated on typical hyperbolic and rotary parts， and the results show that compared with isothermal curing， the curing deformation and residual stress are reduced by nearly 50%； compared with the temperature field optimization method that only considers the curing deformation， the curing deformation and residual stress are also reduced by nearly 15%.
Guanguan CAO , Ke XU . Optimized distortion control method of CFRP curing region temperature field driven by near⁃zero stress equivalent temperature field[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(16) : 429703 -429703 . DOI: 10.7527/S1000-6893.2023.29703
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