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.
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Abbreviations
- C A :
-
axial force coefficient
- C D :
-
drag coefficient
- \(C_{{\rm{mz}}}^{\rm{g}}\) :
-
pitching moment coefficient relative to the center of mass
- C N :
-
normal force coefficient
- ∂C M /∂α :
-
static derivative of the pitching moment
- D :
-
maximum windward diameter/reference length of the entry module (mm)
- H :
-
height (km)
- Kn ∞ :
-
Nosen number of the far field
- L/D :
-
lift-to-drag ratio
- Ma :
-
Mach number
- Ma ∞ :
-
Mach number of the far field
- q,q i :
-
heat flux (kW/m2)
- q 0 :
-
stagnation heat flux at zero angle of attack (kW/m2)
- q c :
-
convective heat flux (kW/m2)
- R :
-
position along the equivalent radial direction of the forebody of the entry module (m)
- X :
-
position along the axial direction of the entry module (m)
- x cg :
-
distance between the longitudinal center of mass and the vertex of the forebody (mm)
- z cg :
-
distance between the horizontal center of mass and the axis (mm)
- α :
-
angle of attack (°)
- α T :
-
trim angle of attack (°)
- β :
-
angle of sideslip (°)
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Acknowledgements
This research comes from the Tianwen-1 Mars exploration mission. The authors gratefully acknowledge the contributions of the entire Tianwen-1 design team.
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Qi Li was graduated from Beihang University in 2008 with a major in fluid mechanics. As the head of the entry and re-entry pneumatic department, she is responsible for the aerodynamic design, analysis and verification of Chang’e-5 and Mars probes. She has won the first prize of Science and Technology Progress of Sichuan Province and the second prize of Science and Technology Progress Award of China Aerospace Science and Technology Corporation.
Wei Rao was graduated from Beihang University in 1993. He participated in the development of Chang’e-1, Chang’e-2 lunar probes and Mars probes, serving as the product assurance manager and deputy designer of the Mars probes. He has won the third prize of National Defense Science and Technology Progress Award once, the special prize of National Science and Technology Progress Award twice, and the National Outstanding Youth, etc.
Xiaoli Cheng has long been engaged in the research of high-temperature real gas effect and rarefied effect.
Haogong Wei achieved his M.S. degree at Purdue University in 2014. Since then he participated in China’s deep space exploration programs at Beijing Institute of Spacecraft System Engineering, focusing on flight dynamics and aerodynamics.
Chuang Wang joined China Academy of Space Technology (CAST) in 2008. His research filed is overall design of deep space probe. He has won one third prize of Science and Technology Progress Award of China Aerospace Science and Technology Corporation and one third prize of Science and Technology Progress Award of Beijing.
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The authors declare that there is no conflict of interest.
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Li, Q., Rao, W., Cheng, X. et al. Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module. Astrodyn 6, 39–52 (2022). https://doi.org/10.1007/s42064-021-0123-z
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DOI: https://doi.org/10.1007/s42064-021-0123-z