Nonlinear dynamics of flexible tethered satellite system subject to space environment

Yu, B.S.; Jin, Dongping; Wen, Hao

doi:10.1007/s10483-016-2049-9

Cited by 21 publications

(8 citation statements)

References 16 publications

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“…where D C is the drag coefficient and S the frontal area of the satellites. r v is the relative velocity of satellites to the atmosphere, which can be obtained by the following expression under the assumption that the atmosphere rotates with the earth r s s = −  E vvω r (17) where s v and s r are the inertial velocity vector and position vector of the satellites, respectively. E ω is the angular velocity of the earth.…”

Section: B Formulations Of Orbital Perturbationsmentioning

confidence: 99%

“…(27).After substitution of the foregoing equations Eqs. (15)(16)(17)(18)(19) that formulate the orbital perturbations into the Eq. ( 27) in a generalized form, dynamic equations of the TSS considering orbital perturbations are obtained.…”

Section: Dynamic Equations Of Tssmentioning

confidence: 99%

“…Space environment would induce an undesired influence on the dynamics of TSS deployment [17]. Numerous investigations have been performed by employing the aforementioned modes of the tether.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Bai

Jiang

2021

IEEE Access

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Orbital perturbations caused by the space environment will induce deviations compared with the prescribed motion trajectory or dynamic performance of the tethered satellite system (TSS). To comprehensively investigate the effects of the orbital perturbations on the TSS, a precise variable-length element that can describe the large deformation and flexibility of the tether is adopted in this paper to predict the deployment dynamics considering orbital perturbations, including atmospheric drag, solar pressure, lunisolar gravitation, and J2 perturbation. To this end, the variable-length element using arbitrary Lagrangian-Eulerian (ALE) description in the frame work of absolute nodal coordinate formulation (ANCF) is developed firstly. Subsequently, the dynamic governing equations for the TSS are established in the context of ANCF with the employment of ANCF reference node (ANCF-RN). Effects of orbital perturbations including atmospheric drag, solar pressure, lunisolar gravity and J2 perturbation on the dynamics of an optimal deployment are analyzed numerically. It is shown that the orbital perturbations except the J2 perturbation will induce the out-of-plane motion of the TSS. Additionally, the tether tension is less affected by the orbital perturbations. By contrast, the lunisolar gravitation will induce a deviation on the motion path of satellite, which should be considered in the design phase of the TSS.

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Section: B Formulations Of Orbital Perturbationsmentioning

confidence: 99%

Section: Dynamic Equations Of Tssmentioning

confidence: 99%

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Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Bai

Jiang

2021

IEEE Access

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“…Actually, the retrieval operation is inherently unstable [2][3][4] . Additionally, the nonlinear dynamics of the problem can generate quasi-periodic and chaotic motions in a two-body TSS [4][5][6][7][8][9][10][11][12][13][14][15][16][17] . Many researchers looked at this problem, investigating the dynamics and control of a TSS during deployment, station keeping, and retrieval stages.…”

Section: Introductionmentioning

confidence: 99%

Controlling Tether Deployment and Retrieval by Lyapunov Approach Involving Quasiperiodic and Chaotic Motions

Salazar

Prado

2022

Preprint

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In the station keeping phase, the in-plane pitch motion of a two body tethered satellite system, that is revolving around the Earth in a Keplerian circular orbit, is similar to the motion of a simple pendulum, i.e. the local vertical position is a center with small oscillations about it, and the local horizontal is a saddle point. However, if the three-dimensional coupled pitch and roll motions are considered, the dynamics of the system exhibit quasi-periodic and chaotic behavior. In order to study the control of the quasiperiodic and chaotic motions of a two-body tethered satellite system, which moves along a Keplerian circular orbit, this paper proposes to suppress the quasi-periodic and chaotic dynamics during deployment and retrieval, by applying a non-linear tension force along the connecting tether. A Lyapunov approach is used to design the non-linear tension for controlling tether deployment and retrieval. The goal of the control is to steer the sub-satellite from quasi-periodic and chaotic states to the local upward vertical position. The numerical simulations show that the non-linear tension control law performs well, reduces the quasi-periodic and chaotic oscillations, and the three-dimensional trajectories can be guided close to the local vertical direction.

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“…In recent years, much interest has been given to the modeling and/or simulation of tethered systems, where the dynamics of interconnected bodies is studied (see, e.g. [26,41,24,25,43,44,40,42,2,32,33]). It turns out that the underlying dynamics is often described by a Hamiltonian system, for which the total energy is conserved.…”

Section: Introductionmentioning

confidence: 99%

Arbitrarily high-order energy-conserving methods for Hamiltonian problems with quadratic holonomic constraints

Amodio¹,

Brugnano²,

Frasca-Caccia³

et al. 2022

Preprint

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Nonlinear dynamics of flexible tethered satellite system subject to space environment

Cited by 21 publications

References 16 publications

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Controlling Tether Deployment and Retrieval by Lyapunov Approach Involving Quasiperiodic and Chaotic Motions

Arbitrarily high-order energy-conserving methods for Hamiltonian problems with quadratic holonomic constraints

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