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Full Length Article | Open Access

Flight dynamics modeling and analysis for a Mars helicopter

Hong ZHAOa,b, Zhiwei DINGa, Gen LENGa,b, Jianbo LIa( )
National Key Laboratory of Helicopter Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
China Helicopter Research & Development Institute, Jingdezhen 33300, China
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Abstract

Flight dynamics modeling for the Mars helicopter faces great challenges. Aerodynamic modeling of coaxial rotor with high confidence and high computational efficiency is a major difficulty for the field. This paper builds an aerodynamic model of coaxial rotor in the extremely thin Martian atmosphere using the viscous vortex particle method. The aerodynamic forces and flow characteristics of rigid coaxial rotor are computed and analyzed. Meanwhile, a high fidelity aerodynamic surrogate model is built to improve the computational efficiency of the flight dynamics model. Results in this paper reveal that rigid coaxial rotor can bring the Mars helicopter sufficient controllability but result in obvious instability and control couplings in forward flight. This highlights the great differences in flight dynamics characteristics compared with conventional helicopters on Earth.

Keywords

Flight dynamicsAerodynamic modelingCoaxial rotorMars helicopterViscous Vortex Particle Method(VVPM)

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Chinese Journal of Aeronautics
Volume 36 Issue 9,
September 2023
Pages 221-230
DOI: 10.1016/j.cja.2023.05.007
Cite this article:
ZHAO H, DING Z, LENG G, et al. Flight dynamics modeling and analysis for a Mars helicopter. Chinese Journal of Aeronautics, 2023, 36(9): 221-230. https://doi.org/10.1016/j.cja.2023.05.007

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Received: 02 August 2022
Revised: 22 December 2022
Accepted: 15 March 2023
Published: 13 May 2023
© 2023 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
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