Open Access
Issue
Published:
04 January 2022
Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module
Download citation
878
Views
74
Downloads
4
Crossref
2
WoS
4
Scopus
1
CSCD
The clear differences between the atmosphere of Mars and the Earth coupled with the lack of a domestic research basis were significant challenges for the aerodynamic prediction and verification of Tianwen-1. In addition, the Mars entry, descent, and landing (EDL) mission led to specific requirements for the accuracy of the aerodynamic deceleration performance, stability, aerothermal heating, and various complex aerodynamic coupling problems of the entry module. This study analyzes the key and difficult aerodynamic and aerothermodynamic problems related to the Mars EDL process. Then, the study process and results of the design and optimization of the entry module configuration are presented along with the calculations and experiments used to obtain the aerodynamic and aerothermodynamic characteristics in the Martian atmosphere. In addition, the simulation and verification of the low-frequency free oscillation characteristics under a large separation flow are described, and some special aerodynamic coupling problems such as the aeroelastic buffeting response of the trim tab are discussed. Finally, the atmospheric parameters and aerodynamic characteristics obtained from the flight data of the Tianwen-1 entry module are compared with the design data. The data obtained from the aerodynamic design, analysis, and verification of the Tianwen-1 entry module all meet the engineering requirements. In particular, the flight data results for the atmospheric parameters, trim angles of attack, and trim axial forces are within the envelopes of the prediction deviation zones.
menu
Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module
Abstract
The clear differences between the atmosphere of Mars and the Earth coupled with the lack of a domestic research basis were significant challenges for the aerodynamic prediction and verification of Tianwen-1. In addition, the Mars entry, descent, and landing (EDL) mission led to specific requirements for the accuracy of the aerodynamic deceleration performance, stability, aerothermal heating, and various complex aerodynamic coupling problems of the entry module. This study analyzes the key and difficult aerodynamic and aerothermodynamic problems related to the Mars EDL process. Then, the study process and results of the design and optimization of the entry module configuration are presented along with the calculations and experiments used to obtain the aerodynamic and aerothermodynamic characteristics in the Martian atmosphere. In addition, the simulation and verification of the low-frequency free oscillation characteristics under a large separation flow are described, and some special aerodynamic coupling problems such as the aeroelastic buffeting response of the trim tab are discussed. Finally, the atmospheric parameters and aerodynamic characteristics obtained from the flight data of the Tianwen-1 entry module are compared with the design data. The data obtained from the aerodynamic design, analysis, and verification of the Tianwen-1 entry module all meet the engineering requirements. In particular, the flight data results for the atmospheric parameters, trim angles of attack, and trim axial forces are within the envelopes of the prediction deviation zones.
References(28)
Geng, Y., Zhou, J. S., Li, S., Fu, Z. L., Meng, L. Z., Liu, J. J., Wang, H. P. Review of first Mars exploration mission in China. Journal of Deep Space Exploration, 2018, 5(5): 399–405. (in Chinese)
Lyu, J. M., Miao, W. B., Cheng, X. L., Wang, Q. Impact of Martian atmosphere model parameters on aerodynamic characteristics of Mars Science Laboratory. Chinese Journal of Space Science, 2014, 34(4): 377–383. (in Chinese)
Rong, W., Chen, G. L. The characters of deceleration and landing technology on Mars explorer. Spacecraft Recovery & Remote Sensing, 2010, 31(4): 1–6. (in Chinese)
Rao, W., Sun, Z. Z., Meng, L. Z., Wang, C., Ji, L. Analysis and design for the Mars entry, descent and landing mission. Journal of Deep Space Exploration, 2016, 3(2): 121–128. (in Chinese)
Willcockson, W. H. Mars pathfinder entry heatshield design and flight experience. Journal of Spacecraft and Rockets, 1999, 36(3): 374–379.
Liang, J., Li, Z. H., Li, Q., Du, B. Numerical simulation of aerodynamic and trim characteristics across different flow regimes for reentry module. Acta Aerodynamica Sinica, 2018, 36(5): 848–855. (in Chinese)
Fang, F., Zhou, L., Li, Z. H. A comprehensive analysis of aerodynamics for spacecraft re-entery Earth's atmosphere surroundings. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 24–38. (in Chinese)
Li, Q., Wei, H. G., Li, Z. H., Chen, G., Peng, J., Yang, M. F. Prediction and flight verification of chemical non-equilibrium aerodynamic characteristics of the high-speed circumlunar return and reentry capsule. SCIENTIA SINICA Technologica, 2015, 51(7): 813–827. (in Chinese)
Lyu, J. M., Cheng, X. L., Wang, Q. Flow field prediction of an orbiter entering the Mars atmosphere. Chinese Journal of Space Science, 2013, 33(2): 129–134. (in Chinese)
Cheng, X. L., Li, J. H., Wang, Q. Aerodynamic force characteristics of Mars entry vehicles. Journal of Astronautics, 2010, 31(4): 967–972. (in Chinese)
Wang, R., Chen, B. Y. Aerodynamic configuration design optimization of reentry capsule based on CFD and multi-objective optimization theory. Acta Aerodynamica Sinica, 2015, 33(5): 588–593, 609. (in Chinese)
Braun, R. D., Manning, R. M. Mars exploration entry, descent, and landing challenges. Journal of Spacecraft and Rockets, 2007, 44(2): 310–323.
Liu, Z. Y., Li, Q., Wei, H. G., Geng, Y. F. Performance comparison of typical semi-ballistic Mars entry vehicles. Acta Aerodynamica Sinica, 2018, 36(5): 863–870. (in Chinese)
Yang, X. F., Tang, W., Gui, Y. W., Xiao, G. M., Feng, Y. Study on aerodynamic configuration of Mars probe. Manned Spaceflight, 2015, 21(4): 412–417. (in Chinese)
Tang, W., Yang, X. F., Gui, Y. W., Du, Y. X. Review of hypersonic aerodynamics and aerothermodynamics for Mars entries. Journal of Astronautics, 2017, 38(3): 230–239. (in Chinese)
Lyu, J. M., Miao, W. B., Huang, F., Cheng, X. L. Model analysis for predicting aerodynamic characteristics of Mars entry. Chinese Journal of Space Science, 2016, 36(3): 344–351. (in Chinese)
Liu, Q. Z., Dong, W. Z., Ding, M. S., Jiang, T., Gao, T. S. Numerical simulation of aerothermal environments and aerodynamic characteristics for Mars entry capsules. Acta Aerodynamica Sinica, 2018, 36(4): 642–650. (in Chinese)
Miao, W. B., Lyu, J. M., Cheng, X. L., Ai, B. C. Numerical analysis of thermodynamics models for Mars entry aeroheating prediction. Chinese Journal of Computational Physics, 2015, 32(4): 410–415. (in Chinese)
Huang, F., Lyu, J. M., Cheng, X. L., Li, Q. Aerodynamics of Mars entry vehicles under hypersonic rarefied condition. Acta Aeronautica et Astronautica Sinica, 2017, 38(5): 120457. (in Chinese)
Publication history
Copyright
Acknowledgements
This research comes from the Tianwen-1 Mars exploration mission. The authors gratefully acknowledge the contributions of the entire Tianwen-1 design team.
Rights and permissions
Open Access This article is licensed under a Creative Commons Attribution 4.0 International License, which permits use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons licence, and indicate if changes were made.
The images or other third party material in this article are included in the article's Creative Commons licence, unless indicated otherwise in a credit line to the material. If material is not included in the article's Creative Commons licence and your intended use is not permitted by statutory regulation or exceeds the permitted use, you will need to obtain permission directly from the copyright holder.
To view a copy of this license, visit http://creativecommons.org/licenses/by-nc-sa/4.0/
FEEDBACK 
TOP