Acta Mechanica Sinica

, Volume 33, Issue 1, pp 208–218

Analytical method for the attitude stability of partially liquid filled spacecraft with flexible appendage

Research Paper

DOI: 10.1007/s10409-016-0616-9

Cite this article as:
Yan, Y. & Yue, B. Acta Mech. Sin. (2017) 33: 208. doi:10.1007/s10409-016-0616-9
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Abstract

In this paper, the attitude stability of liquid-filled spacecraft with flexible appendage is investigated. The motion of liquid sloshing is modeled as the spherical pendulum, and the flexible appendage is approached by a linear shearing beam. Nonlinear dynamic equations of the coupled system are derived from the Hamiltonian. The stability of the coupled system was analyzed by using the energy-Casimir method, and the nonlinear stability theorem of the coupled spacecraft system was also obtained. Through numerical computation, the correctness of the proposed theorem is verified and the boundary curves of the stable region are presented. The increase of the angular velocity and flexible attachment length will weaken the attitude stability, and the change of the filled ratio of liquid fuel tank has a different influence on the stability of the coupled spacecraft, depending on the different conditions. The attitude stability analysis of the coupled spacecraft system in this context is useful for selecting appropriate parameters in the complex spacecraft design.

Keywords

Liquid-filled spacecraft Energy-Casimir method Flexible attachment Stability analysis 

Copyright information

© The Chinese Society of Theoretical and Applied Mechanics; Institute of Mechanics, Chinese Academy of Sciences and Springer-Verlag Berlin Heidelberg 2016

Authors and Affiliations

  1. 1.School of Aerospace EngineeringBeijing Institute of TechnologyBeijingChina

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