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    188宝金博页面版: Long-term dynamic modeling of tethered spacecraft,Long-term dynamic modeling of tethered spacecraft

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    内容提示： Celest Mech Dyn Astr (2015) 123:363–386DOI 10.1007/s10569-015-9640-5ORIGINAL ARTICLELong-term dynamic modeling of tethered spacecraftusing nodal position finite element method and symplecticintegrationG. Q. Li1,2· Z. H. Zhu2Received: 14 August 2014 / Revised: 9 May 2015 / Accepted: 10 July 2015 /Published online: 27 August 2015? Springer Science+Business Media Dordrecht 2015Abstract Dynamic modeling of tethered spacecraft with the consideration of elasticity oftether is prone to the numerical instabilit...

    文档格式：PDF | 页数：24 | 浏览次数：36 | 上传日期：2015-10-28 20:40:05 | 文档星级：
    Celest Mech Dyn Astr (2015) 123:363–386DOI 10.1007/s10569-015-9640-5ORIGINAL ARTICLELong-term dynamic modeling of tethered spacecraftusing nodal position finite element method and symplecticintegrationG. Q. Li1,2· Z. H. Zhu2Received: 14 August 2014 / Revised: 9 May 2015 / Accepted: 10 July 2015 /Published online: 27 August 2015© Springer Science+Business Media Dordrecht 2015Abstract Dynamic modeling of tethered spacecraft with the consideration of elasticity oftether is prone to the numerical instability and error accumulation over long-term numericalintegration. This paper addresses the challenges by proposing a globally stable numericalapproach with the nodal position finite element method (NPFEM) and the implicit, symplec-tic, 2-stage and 4th order Gaussian–Legendre Runge–Kutta time integration. The NPFEMeliminates the numerical error accumulation by using the position instead of displacementof tether as the state variable, while the symplectic integration enforces the energy andmomentum conservation of the discretized finite element model to ensure the global sta-bility of numerical solution. The effectiveness and robustness of the proposed approach isassessedbyanelasticpendulumproblem,whosedynamicresponseresemblesthatoftetheredspacecraft, in comparison with the commonly used time integrators such as the classical 4thorder Runge–Kutta schemes and other families of non-symplectic Runge–Kutta schemes.Numerical results show that the proposed approach is accurate and the energy of the corre-sponding numerical model is conservative over the long-term numerical integration. Finally,the proposed approach is applied to the dynamic modeling of deorbiting process of tetheredspacecraft over a long period.KeywordsTethered spacecraft · Dynamics · Elastic tether · Nodal position finite elementmethod · Symplectic integration · Satellite deorbitB Z. H. Zhugzhu@yorku.ca1School of Aeronautics and Astronautics, Shanghai Jiao Tong University, 800 Dongchuan Rd,Shanghai 200230, China2Department of Earth and Space Science and Engineering, York University, 4700 Keele Street,Toronto, ON M3J 1P3, Canada123

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