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Attitude Motion of a Spinning Spacecraft with Fuel Sloshing and Nutation Damping

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Abstract

We use Kane’s method to derive the equations of motion of a spinning spacecraft with three momentum wheels, a nutation damper, and a spherical pendulum. The spherical pendulum is adopted as a simple mechanical equivalent of fuel sloshing in partially filled tanks. The proposed model is an extension of existing models in the literature. We verify and validate our model for two cases: flat spin and a simple reorientation maneuver. Numerical simulations are in agreement with existing results in the literature. The results confirm the accuracy of the model for a typical spacecraft.

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Authors and Affiliations

  1. Department of Mechanical Engineering, Santa Clara University, CA, 95053-0575, USA

    Mohammad A. Ayoubi (Assistant Professor) & Farhad A. Goodarzi (Formerly, Graduate Student)

  2. Lockheed Martin Advanced Technology Center, Palo Alto, CA, 94305, USA

    Arun Banerjee (Formerly Principal Research Scientist)

Authors
  1. Mohammad A. Ayoubi
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  2. Farhad A. Goodarzi
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  3. Arun Banerjee
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Correspondence to Mohammad A. Ayoubi.

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Ayoubi, M.A., Goodarzi, F.A. & Banerjee, A. Attitude Motion of a Spinning Spacecraft with Fuel Sloshing and Nutation Damping. J of Astronaut Sci 58, 551–568 (2011). https://doi.org/10.1007/BF03321531

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  • DOI: https://doi.org/10.1007/BF03321531

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