Composite Carbon–Epoxy Tubes for Space Structures: Ground Vacuum Radiant Experiments and Structural Behavior Analysis
Publication: Journal of Aerospace Engineering
Volume 32, Issue 6
Abstract
The utilization of composite carbon–epoxy tubes for space structures, such as antennas and solar arrays, has attracted considerable attention in recent decades due to their high strength-to-weight ratio and multifunctional applications. Among complex space environmental factors, thermal effects induced by uneven solar irradiance could generate temperature stress, cause thermal behavior and affect the guidance and control of spacecraft structures. In this paper, a series of temperature experiments for the identification of material properties and ground vacuum radiant experiments for the determination of the structural behavior of a composite carbon–epoxy tube are carried out with respect to space environments. Moreover, numerical models on the basis of experimental observations are developed to investigate corresponding thermal and structural behavior. It is found that the specific heat and thermal conductivity of two typical specimens increase linearly with temperature rise and are dependent on carbon directions. For thermal and structural experiments, a significant temperature difference of 30°C exists between top and bottom surfaces resulting from different radiation and heat conduction. A temperature difference of 8.7°C is found in the thick direction on the bottom surface, which could result in noticeable shear deformation during the service period. Average strains on top and bottom surfaces are and , respectively. Furthermore, numerical temperatures on the top surface are in good agreement with experimental results, while those on the bottom surface are higher than experimental temperatures due to the radiant effects of the chamber and complex interactions between the tube and tracks. A further numerical analysis on the thermal and structural behavior of the supporting frame could provide guidance for designing future corresponding structures.
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Acknowledgments
This work was supported by the National Natural Science Foundation of China (51608320, 51478264, and 11172180) and a project funded by the China Postdoctoral Science Foundation (2017T100298 and 2016M591677). The authors are grateful to the editors and anonymous reviewers for their professional comments and suggestions for improving the quality of the paper.
References
Bainum, P., N. Hamsath, and R. Krishna. 1989. “The dynamics and control of large space structures after the onset of thermal shock.” Acta Astronaut. 19 (1): 1–8. https://doi.org/10.1016/0094-5765(89)90002-7.
Beam, R. M. 1969. On the phenomenon of thermoelastic instability/thermal flutter/of booms with open cross section. Wasington, DC: National Aeronautics and Space Administration.
Boleyt, B. A. 1956. “Thermally induced vibrations of beams.” J. Aeronaut. Sci. 23 (2): 179–181.
Chen, H., V. V. Ginzburg, J. Yang, Y. Yang, W. Liu, Y. Huang, L. Du, and B. Chen. 2016. “Thermal conductivity of polymer-based composites: Fundamentals and applications.” Prog. Polym. Sci. 59 (Aug): 41–85. https://doi.org/10.1016/j.progpolymsci.2016.03.001.
Chen, W., G. Fang, and Y. Hu. 2017. “An experimental and numerical study of flattening and wrapping process of deployable composite thin-walled lenticular tubes.” Thin-Walled Struct. 111 (Feb): 38–47. https://doi.org/10.1016/j.tws.2016.11.009.
Chen, W., and S. Zhang. 2006. Deployable space structures and analysis theory. Beijing: China Astronautic Publishing House.
Cheng, X. 2011. Thermal analysis of space inflatable deployment sclerosis film antenna structures. Shanghai: Shanghai Jiao Tong Univ.
Graham, J. D. 1970. “Solar induced bending vibrations of a flexible member.” AIAA J. 8 (11): 2031–2036. https://doi.org/10.2514/3.6042.
Hu, Y., W. Chen, J. Gao, J. Hu, G. Fang, and F. Peng. 2017. “A study of flattening process of deployable composite thin-walled lenticular tubes under compression and tension.” Compos. Struct. 168 (May): 164–177. https://doi.org/10.1016/j.compstruct.2017.02.029.
Johnston, J. D., and E. A. Thornton. 2000. “Thermally induced dynamics of satellite solar panels.” J. Spacecraft Rockets 37 (5): 604–613. https://doi.org/10.2514/2.3633.
Ko, K.-E., and J.-H. Kim. 2003. “Thermally induced vibrations of spinning thin-walled composite beam.” AIAA J. 41 (2): 296–303. https://doi.org/10.2514/2.1943.
Liu, J. 2013. “Thermal-structural analysis for support structure of deployable space antenna.” Master thesis, Dept. of Civil Engineering, Shanghai Jiao Tong Univ.
Liu, J., W. Chen, G. Fang, and F. Peng. 2012. “Structural performance of carbon/epoxy thin-walled tabular boom under space radiantly heating.” [In Chinese.] J. Sichuan Ordnance 33 (11): 124–128.
Lutz, J., D. Allen, and W. Haisler. 1987. “Finite-element model for the thermoelastic analysis of large composite space structures.” J. Spacecraft Rockets 24 (5): 430–436. https://doi.org/10.2514/3.25935.
Mazur, E., D. Matteo, and R. Oxenreider. 1966. Passive damper bearing and gravity-gradient rod development. Washington, DC: National Aeronautics and Space Administration.
Morozov, E., A. Lopatin, and V. Taygin. 2016. “Design, analysis, manufacture and testing of composite corrugated horn for the spacecraft antenna system.” Compos. Struct. 136 (Feb): 505–512. https://doi.org/10.1016/j.compstruct.2015.11.004.
Olmstead, W., and S. Raynor. 1962. “Solar heating of a rotating spherical space vehicle.” Int. J. Heat Mass Transfer 5 (12): 1165–1177. https://doi.org/10.1016/0017-9310(62)90192-8.
Rait, G., and D. Beasley. 2017. “Large area membrane apertures for space applications, fabrication and mechanical testing.” In Proc., 4th AIAA Spacecraft Structures Conf. Reston, VA: American Institute of Aeronautics and Astronautics.
Soliman, H. E., and T. Stoumbos. 2014. “FEM correlation of sandwich composite antenna structure subject to thermal distortion.” In Proc., 55th AIAA/ASMe/ASCE/AHS/SC Structures, Structural Dynamics, and Materials Conf. Reston, VA: American Institute of Aeronautics and Astronautics.
Song, O., I. Yoon, and L. Librescu. 2003. “Thermally induced bending vibration of composite spacecraft booms subjected to solar heating.” J. Therm. Stresses 26 (8): 829–843. https://doi.org/10.1080/01495730306307.
Thornton, E. A. 1996. Thermal structures for aerospace applications. Reston, VA: American Institute of Aeronautics and Astronautics.
Thornton, E. A., and Y. A. Kim. 1993. “Thermally induced bending vibrations of a flexible rolled-up solar array.” J. Spacecraft Rockets 30 (4): 438–448. https://doi.org/10.2514/3.25550.
Thornton, E. A., and D. B. Paul. 1985. “Thermal-structural analysis of large space structures—An assessment of recent advances.” J. Spacecraft Rockets 22 (4): 385–393. https://doi.org/10.2514/3.25761.
Vigneron, F. 1970. “Thermal curvature time constants of thin-walled tubular spacecraft booms.” J. Spacecraft Rockets 7 (10): 1256–1259. https://doi.org/10.2514/3.30147.
Yu, Y.-Y. 1969. “Thermally induced vibration and flutter of a flexible boom.” J. Spacecraft Rockets 6 (8): 902–910. https://doi.org/10.2514/3.29725.
Zhang, J., Z. Xiang, Y. Liu, and M. Xue. 2014. “Stability of thermally induced vibration of a beam subjected to solar heating.” AIAA J. 52 (3): 660–665. https://doi.org/10.2514/1.J052574.
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Published In
Journal of Aerospace Engineering
Volume 32 • Issue 6 • November 2019
Copyright
©2019 American Society of Civil Engineers.
History
Received: Jan 10, 2018
Accepted: May 11, 2018
Published online: Jul 31, 2019
Published in print: Nov 1, 2019
Discussion open until: Dec 31, 2019
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