TY - JOUR
T1 - Stability analysis of coupled orbit-attitude dynamics around asteroids using finite-time Lyapunov exponents
AU - Kikuchi, Shota
AU - Tsuda, Yuichi
AU - Yoshikawa, Makoto
AU - Jun'ichiro, Kawaguchi
N1 - Funding Information:
This work was supported by Grants-in-Aid for Scientific Research (18H05901) from the Japan Society for the Promotion of Science. We thank Kathleen C. Howell of Purdue University, who provided insight that greatly assisted this research. Previous version of this paper was presented as Paper 17-823 at the AAS/AIAA Astrodynamics Specialist Conference, Stevenson, Washington, 20-24 August 2017.
Funding Information:
This work was supported by Grants-in-Aid for Scientific Research (18H05901) from the Japan Society for the Promotion of Science. We thank Kathleen C. Howell of Purdue University, who provided insight that greatly assisted this research. Previous version of this paper was presented as Paper 17-823 at the AAS/AIAA Astrodynamics Specialist Conference, Stevenson, Washington, 20–24 August 2017.
Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2019
Y1 - 2019
N2 - This paper investigates coupled orbit-attitude dynamics around asteroids subject to solar radiation pressure and gravity irregularities. The solutions of sun-synchronous orbits with sun-tracking attitude motion are analytically derived, and their stability is evaluated by applying linearization and averaging. To validate the analytical solutions, numerical simulations are performed based on nonlinear coupled orbit-attitude equations of motion. In addition, the nonlinear stability of such coupled motion is analyzed using finite-time Lyapunov exponents. It is demonstrated that the sun-synchronous orbit-attitude coupled motions exhibit long-term stability under certain conditions, and thus, these motions are promising options for asteroid missions.
AB - This paper investigates coupled orbit-attitude dynamics around asteroids subject to solar radiation pressure and gravity irregularities. The solutions of sun-synchronous orbits with sun-tracking attitude motion are analytically derived, and their stability is evaluated by applying linearization and averaging. To validate the analytical solutions, numerical simulations are performed based on nonlinear coupled orbit-attitude equations of motion. In addition, the nonlinear stability of such coupled motion is analyzed using finite-time Lyapunov exponents. It is demonstrated that the sun-synchronous orbit-attitude coupled motions exhibit long-term stability under certain conditions, and thus, these motions are promising options for asteroid missions.
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U2 - 10.2514/1.G003879
DO - 10.2514/1.G003879
M3 - Article
AN - SCOPUS:85065584430
SN - 0731-5090
VL - 42
SP - 1289
EP - 1305
JO - Journal of Guidance, Control, and Dynamics
JF - Journal of Guidance, Control, and Dynamics
IS - 6
ER -