Nonlinear dynamic analysis of a three-body tethered satellite system with deployment/retrieval

Jung, Wonjin; Mazzoleni, Andre P.; Chung, Jintai

doi:10.1007/s11071-015-2221-z

Cited by 62 publications

(13 citation statements)

References 17 publications

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“…The deployment of a three-body tethered satellite system is carried out with the control method of (25), which is similar with methods described in [18,22] and (26), respectively. The former method is denoted as the first method while the latter one is regarded as the second method.…”

Section: Control Methods Of Deploymentmentioning

confidence: 99%

“…Alary et al focused their attention on the dynamics of a multitethered pyramidal formation and proposed a control strategy in order to stabilize the system [17]. The dynamic behavior of a three-body tethered satellite system was parametrically analyzed under several groups of initial satellite attitudes by Jung et al [18]. To the author's knowledge, most attention was focused on the dynamics model and stability around the nominal position, that is, the equilibrium situation, and control methods, which intend to stabilize the system to the equilibrium position.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Separation Strategy on Deployment of Multitethered Chain-Type Satellite System

Zhang

2016

Mathematical Problems in Engineering

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This paper investigates the effects of separation strategy and parameters related to deployment on the dynamic behavior of multitethered chain-type satellite system. The system, including several satellites connected by tethers which are considered as massless and straight, is modeled as an extension of a two-body dumbbell tethered system. The dynamic equations of system in absence of perturbations and external disturbances are derived using Newtonian Method. To observe the effect of deployment rate on the motion of system, a parametric analysis of the deployment of a three-body tethered system with different deployment rates is carried out. Moreover, a four-body tethered system is used to investigate the effect of separation strategies on the dynamic behavior of system during the deployment phase. The numerical results suggest that the system with simultaneous separation costs less time to complete the deployment. If the ratio of deployment rates is in consistence with that of their desired lengths, the tethers deployed simultaneously would have a synchronous motion. It is also observed that the system employing separation bolt has a better performance than the system separated by spring mechanism since the larger separation velocity which is not along local vertical may cause a rotation.

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Section: Control Methods Of Deploymentmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effects of Separation Strategy on Deployment of Multitethered Chain-Type Satellite System

Zhang

2016

Mathematical Problems in Engineering

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“…Ishimura and Higuchi (2008) proposed an elastic rod model for some components of the tethered space solar power satellite (SSPS) system and studied the coupling dynamic behaviors among the orbital motion, pitching motion, and axial vibration numerically by linearizing the differential equation. Jung et al (2014Jung et al ( , 2015 proposed a dumbbell model for the tethered satellite system and performed the nonlinear dynamic analysis of a three-body tethered satellite system undergoing the deployment and retrieval process. Zhang et al (2015) proposed the modelling process for the spatial flexible beam, which gave some inspiration for the dynamic system considered in this study.…”

Section: Introductionmentioning

confidence: 99%

Symplectic analysis on orbit-attitude coupling dynamic problem of spatial rigid rod

Wei

Deng

2020

Journal of Vibration and Control

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An orbit-attitude coupling dynamic model for the spatial rigid rod that is abstracted from the large-stiffness slender components widely used in spatial structures is established, and the symplectic method is used to estimate the validity of the dynamic model by analyzing the coupling dynamic behaviors of the rod in this work. Based on the Hamiltonian variational principle, the orbit-attitude dynamic model of the spatial rigid rod is proposed, and the canonical form of the model is presented first. Then, the symplectic Runge–Kutta method is developed, and the structure-preserving properties of the canonical form, including the conservation law of energy and conservative property in the phase space, are investigated to illustrate the validity of the numerical results obtained by the symplectic Runge–Kutta method subsequently. Finally, the effects of the nonspherical perturbations of the Earth on the coupling dynamic behaviors are investigated numerically. From the simulation results, it can be concluded that the main orbit-attitude coupling dynamic behaviors of the spatial large-stiffness slender component excited by the nonspherical perturbation can be described by the proposed dynamic model ignoring the deformation as well as the transverse vibration of the slender component, which provides an approach for simplifying rapid dynamic analysis on the spatial large-stiffness slender component. In addition, the validity and the structure-preserving properties of the symplectic Runge–Kutta method for the orbit-attitude coupling dynamic problem of the spatial rigid rod are also illustrated.

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“…Huang et al 19 studied the combination of tethered robots by the means of thruster control, which provided constant force to make the entire system stable. Some other classical control methods, such as LQG 20 and non-linear dynamic control 21 were adopted to implement the thruster-aid control for deployment of TSS. Besides these controllers, since thrusters make the system decoupled and actuated, distributed control 22 and sliding PID control 23 are also the potential methodologies theoretically.…”

Section: Introductionmentioning

confidence: 99%

Pure-tension non-linear sliding mode control for deployment of tethered satellite system

Sun

Cheng

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents a sliding mode controller for the deployment of two-body tethered satellite system. A sliding surface design for underactuated system is employed to reconcile pure-tension control scheme with non-linear coupled deployment dynamics. The proposed sliding surface is strictly non-linear. Hence, the control scheme does not require linearization operation of tethered satellite system and can guarantee that all the system states converge to zero with arbitrary small errors. To deal with input constraint of pure-tension control, an adaption is introduced into the controller design to remove the negative effect caused by input constraint in stability analyses and ensures the feasibility of the proposed controller even though command input overtakes the tolerance of tension actuator. To avoid the chattering phenomena, the trivial sign function is removed from the switching input and replaced by the disturbance observer. Numerical results demonstrate the effectiveness of the proposed controller for the deployment of the tethered satellite system.

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Nonlinear dynamic analysis of a three-body tethered satellite system with deployment/retrieval

Cited by 62 publications

References 17 publications

Effects of Separation Strategy on Deployment of Multitethered Chain-Type Satellite System

Effects of Separation Strategy on Deployment of Multitethered Chain-Type Satellite System

Symplectic analysis on orbit-attitude coupling dynamic problem of spatial rigid rod

Pure-tension non-linear sliding mode control for deployment of tethered satellite system

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