Numerical Method of Symplectic State Transition Matrix and Application to Fully Perturbed Earth Orbit
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- TSUDA Yuichi
- The Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
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- SCHEERES Daniel J.
- Department of Aerospace Engineering Sciences, The University of Colorado at Boulder
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説明
This paper presents a numerical method for deriving a symplectic state transition matrix for high-fidelity Earth orbits subject to non-dissipative perturbation forces. By taking advantage of properties of Hamiltonian systems, this method provides an exact solution space mapping of linearized orbital dynamics, preserving the symplectic structure that all Hamiltonian systems should possess by nature. This method can be applied to accurate, yet computationally efficient dynamic filters, long-term propagations of the motions of formation flying spacecraft and the eigenstructure analysis of N-body dynamics, etc., when the exact structure-preserving property is crucial. We show the derivation of the numerical method of symplectic state transition matrix, and apply it to Earth orbits with perturbation forces based on real ephemerides. These numerical examples reveal that this method shows improvements in preserving the structural properties of the state transition matrix, and in the computational efficiency compared to the conventional linear state transition matrix with Euler or Runge-Kutta integration.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53 (180), 105-113, 2010
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001204080373888
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- NII論文ID
- 10026612992
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- NII書誌ID
- AA0086707X
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- ISSN
- 21894205
- 05493811
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- NDL書誌ID
- 10782709
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- NDL
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