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Acta Aeronautica et Astronautica Sinica ›› 2023, Vol. 44 ›› Issue (19): 228337-228337.doi: 10.7527/S1000-6893.2023.28337

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

Thermal⁃structure coupling characteristics of flexible envelopes for stratospheric airships at float conditions

Zhenyu MA(), Xiaolong DENG, Xixiang YANG, Bingjie ZHU   

  1. College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China
  • Received:2022-11-30 Revised:2023-02-14 Accepted:2023-04-07 Online:2023-10-15 Published:2023-04-07
  • Contact: Zhenyu MA E-mail:mazhenyu@nudt.edu.cn
  • Supported by:
    National Natural Science Foundation of China(51605484);National Science and Technology Major Project(GFZX040201)

Abstract:

A three-dimensional transient thermal model for stratospheric airships during floating is developed, considering the effects of solar radiation, infrared radiation, internal and external convective heat transfer, and solar array heat transfer. The finite element model of the envelope structure for stratospheric airships is established, taking into account the characteristics of thin-film wrinkles and inflation status. Based on the model validations, the computational method of thermal-structure coupling is proposed according to the partitioned coupling strategy. The thermal-structure coupling characteristics of stratospheric airships at float conditions during day and night are simulated and analyzed to obtain the distributions of temperature, deformation and stress of envelopes and their temporal variation rules. The computational results show that solar radiation and solar array heat transfer characteristics have significant effects on the temperature distribution, deformation, and stress of envelopes. Under design conditions, the maximum temperature difference reaches 60 K at the layout boundary of the solar array, the maximum radial displacement at the top of envelopes during daytime reaches 1.5 m, and the maximum axial stress and the maximum circumferential stress at the layout boundary of the solar array are approximately 82 MPa and 140 MPa, respectively. There are obvious wrinkle deformations in the middle of envelopes with the wrinkle amplitude reaching 1.1 m below the horizontal symmetry plane at night under lower differential pressure conditions, which has important impacts on the structural performance of envelopes for stratospheric airships.

Key words: thermal-structure coupling, finite element method, flexible envelopes, stratospheric airships, float conditions

CLC Number: