Long-term dynamic modeling of tethered spacecraft using nodal position finite element method and symplectic integration

DOI10.1007/s10569-015-9640-5zbMath1331.70067OpenAlexW2172473432WikidataQ59104546 ScholiaQ59104546MaRDI QIDQ5964714

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Publication date: 1 March 2016

Published in: Celestial Mechanics and Dynamical Astronomy (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1007/s10569-015-9640-5

zbMATH Keywords

dynamicssymplectic integrationelastic tethernodal position finite element methodsatellite deorbittethered spacecraft

Mathematics Subject Classification ID

Two-body problems (70F05) Finite element, Rayleigh-Ritz and Galerkin methods for initial value and initial-boundary value problems involving PDEs (65M60) Orbital mechanics (70M20) Numerical methods for Hamiltonian systems including symplectic integrators (65P10)

Related Items (4)

Stability and control of radial deployment of electric solar wind sail ⋮ A high accurate Hamiltonian nodal position finite element method for spatial cable structures undergoing long-term large overall motion ⋮ Rigid-flexible coupling effect on attitude dynamics of electric solar wind sail ⋮ Coupled orbit-attitude dynamics of tethered-SPS

Cites Work

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