Deployment of flexible space tether system with satellite attitude stabilization

Cheng-xin, Luo; Wen, Hao; Jin, Dongping

doi:10.1016/j.actaastro.2019.04.036

Cited by 24 publications

(10 citation statements)

References 34 publications

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“…Thus, Eq. (5) can be transformed into a compact form and is expressed as , ( 1,2) Herein the D'Alembert's principle is used to derive the motion governing equations due to its application in time-varying system. For the variable-length tether element of length l , the total virtual work done by all external forces and inertial forces in an arbitrary virtual displacement should be vanished ( )…”

Section: A Dynamic Equations Of Variable-length Tethermentioning

confidence: 99%

“…Recent decades, increasing attentions have been paid to the tethered satellite system (TSS) with respect to tether dynamics [1], satellite attitude stabilization [2], control strategy [3] . With two or more satellites connected together with the tether, the TSS has wide applications in artificial gravity [4], deep space observation [5], orbital transferring [6], space debris retrieval [7], and so on.…”

Section: Introductionmentioning

confidence: 99%

“…Further, considering the space environment including the J2 perturbation, the atmospheric drag, and solar pressure, an analytical control low of the tether was presented [22]. Attitude stabilization of the satellite during flexible tether deployment that taking account of the J2 perturbation forces was investigated [2].…”

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: A Dynamic Equations Of Variable-length Tethermentioning

confidence: 99%

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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“…Ultimately,f l remains stable with a static error " l ¼ 1:5, while the network approximation error of f is much smaller, which is " ¼ 0:2. The approximation errors for f l and f can be accounted for by the reasons below: (i) The static errors contain the approximation errors of the RBF neural network structure " j , as shown in equations (16) and (17), which causes the existence of the deviation between the estimation and the value of the function; (ii) Instead of " j ,W T j h j x, x 0 ð Þ also have a contribution to cause the deviation because the error of weightsW j can only be proved bounded according to the aforementioned analysis based on the Lyapunov theorem. Consequently, the total approximation errorsf j x, x 0 ð Þ are the superimposition of the errors caused by the terms " j andW T j h j x, x 0 ð Þ.…”

Section: Numerical Simulation Analysismentioning

confidence: 99%

“…The satellite stabilization and tether deployment were simultaneously controlled and the tension feedback controller was used to track the optimized deployment trajectory. 17 Sliding mode control (SMC) was adopted to realize robust trajectory tracking. 18 Recently, SMC has been used for the tether deployment problem for its adaptability in the face of model uncertainties and exogenous disturbances.…”

Section: Introductionmentioning

confidence: 99%

Neural network-based adaptive terminal sliding mode control for the deployment process of the dual-body tethered satellite system

Liu

Wang

Guo

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The dual-body tethered satellite system, which consists of two spacecraft connected by a single tether, is one of the most promising configurations in numerous space missions. To ensure the stability of deployment, the radial basis function neural network-based adaptive terminal sliding mode controller is proposed for the dual-body tethered satellite system with the model uncertainty and external disturbance. The terminal sliding mode controller serves as the main control framework for its properties of the strong robustness and finite-time convergence. The radial basis function neural network is adopted to approximate the model uncertainty, in which the weight vector of the radial basis function neural networks and the unknown upper bound of the external disturbance are estimated by using two adaptive laws. Finally, the Lyapunov theory and numerical simulations are used to prove the validity of the proposed controller.

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Observer‐based robust control for N‐coupled wave equations

Meng

Guo

2023

Intl J Robust & Nonlinear

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In this article, we consider robust output regulation for an MIMO wave system with disturbance and reference produced from an exosystem. The approach we adopt is the observer‐ based approach from partial differential equation (PDE) perspective. The main differences from our previous works are two points: (a) the eigenvalues of the exosystem are not necessarily required to be algebraically simple; (b) tracking error feedback dynamic controls are designed directly from the uncertain PDE itself, not a nominal system where disturbance and reference are specially chosen so that the nominal waves and exosystem are detectable. To this purpose, we introduce transformations to transfer the original system into a disturbance free system, and at the same time, each reference is transformed into a linear combination of the exosystem. An observer is designed to estimate the states of the transformed disturbance free system and the unknown linear combinations of the exosystem. The feedforward controls are designed where the input disturbances are then written based on the linear combinations of the exosystem. A set of observer‐based feedback controls is then designed by replacing the state and disturbance with their estimates from the observer. The robustness of the closed‐loop system is discussed by analyzing the stability of the transformed tracking error system and the observer error system. The numerical simulations are presented to validate visually the effectiveness of the proposed tracking error feedback control.

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Deployment of flexible space tether system with satellite attitude stabilization

Cited by 24 publications

References 34 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

Neural network-based adaptive terminal sliding mode control for the deployment process of the dual-body tethered satellite system

Observer‐based robust control for N‐coupled wave equations

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