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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (7): 625438-625438.doi: 10.7527/S1000-6893.2021.25438

• Special Topic of Advanced Manufacturing Technology and Equipment • Previous Articles    

Preparation and evaluation of carbon fiber/polyimide composite attaching collars based on high temperature resin transfer mould process

LUO Chuyang1,2, JIANG Shengda1, CHEN Mengxiong1, ZHANG Peng3, XIA Xufeng2, CAI Peipei2   

  1. 1. Collaborative Innovation Center for Civil Aviation Composites, Donghua University, Shanghai 201620, China;
    2. China Airborne Missile Academy, Luoyang 471009, China;
    3. Science and Technology on Advanced Composites Laboratory, AVIC Composite Technology Center, Beijing 101300, China
  • Received:2021-03-02 Revised:2021-04-06 Published:2021-04-29
  • Supported by:
    Aeronautical Science Foundation of China (20180112008); Young Elite Scientist Sponsorship Program (2016QNRC001); Science and Technology Commission of Shanghai Municipality (19DZ1100300)

Abstract: A carbon fiber/polyimide composite attaching collar was designed and manufactured by high temperature Resin Transfer Mould (RTM) process according to the structural characteristics of attaching collars and the mechanical properties and forming process requirements of composite materials. The ultrasonic inspection results showed the good internal quality of the composite attaching collar. The static strength test conducted at room temperature showed that the maximum strain of the composite attaching collar is -491.0 με, indicating that the composite attaching collar maintains structural integrity under 150% ot the design load and meets the static strength design requirements. The thermo-static mechanical coupling test results at the maximum service temperature of 520 ℃ revealed that the attaching collar failed under the limit load of 118% due to the rapture of the screws at the root. The finite element analysis showed that the maximum stress of the composite attaching collar at room temperature occurred at the edge of the holes, and the primary failure mode was crushing and interlaminar shear failure around the holes. In comparison, the primary damage of the composite attaching collar at high temperature appeared at the outer thermal protection layer and the holes, which has minor influence on the structure bearing.

Key words: polyimide composite, Resin Transfer Molding (RTM), thermal structure of high-speed aircraft, thermo-static mechanical coupling test, finite element analysis

CLC Number: