张春雨, 吕凯, 张宗华, 朱华, 顾志悦. 碳纤维承力筒一体化结构设计及试验验证[J]. 航天器环境工程, 2014, 31(2): 186-190 DOI: 10.12126/see.2014.02.015
引用本文: 张春雨, 吕凯, 张宗华, 朱华, 顾志悦. 碳纤维承力筒一体化结构设计及试验验证[J]. 航天器环境工程, 2014, 31(2): 186-190 DOI: 10.12126/see.2014.02.015
Zhang Chunyu,. Integrated structural design and experimental verification of cylinder made of carbon fiber composite material[J]. Spacecraft Environment Engineering, 2014, 31(2): 186-190. DOI: 10.12126/see.2014.02.015
Citation: Zhang Chunyu,. Integrated structural design and experimental verification of cylinder made of carbon fiber composite material[J]. Spacecraft Environment Engineering, 2014, 31(2): 186-190. DOI: 10.12126/see.2014.02.015

碳纤维承力筒一体化结构设计及试验验证

Integrated structural design and experimental verification of cylinder made of carbon fiber composite material

  • 摘要: 为了减小卫星结构质量并保持良好的力学传递性能,文章在不改变原中心承力筒构型和外部接口的情况下,对碳纤维T800H树脂基复合材料的桁条加筋承力筒进行了锥柱一体化的结构设计,包括:采用可行方向法优化了承力筒的尺寸,确定了蒙皮单层铺层厚度和铺层方式,对端框进行了一体化的设计,以及各部件采用胶接的方式。优化后的承力筒结构质量减小约52.4%。对该承力筒在整星状态下进行相应的力学分析,完成了承力筒静力试验和整星的振动试验,结果表明,该承力筒的结构性能满足使用要求。

     

    Abstract: For reducing the weight of a satellite and enhancing its mechanical transfer performance, the carbon fiber T800H resin matrix composite material is used for the conical-columned integrated structural design of the stringer stiffened cylinder according to the actual demands of developing the satellite, the size of the cylinder is optimized, the thickness of the envelope and the stacking sequences are defined, the integrated joint frames are designed, and the adhesive technique is adopted in jointing parts of the cylinder. After the structural optimization design, the mass of the cylinder is reduced by about 52.4%. Meanwhile, the corresponding mechanical analysis is performed for the full satellite. The static test of the cylinder and the vibration test of the full satellite are carried out. It is shown that the cylinder can satisfy the technical requirements.

     

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