Dynamics of Tethered Space Systems

Алпатов, А.П.; Beletsky, V. V.; Dranovskii, V. I.; Khoroshilov, V. S.; Pirozhenko, A.V.; Tröger, H.; Zakrzhevskii, A. E.

doi:10.1201/9781439836866

Cited by 28 publications

(15 citation statements)

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“…al. 4 They describe the perturbation influence via the change of tether tension as function of the tether dimensions (length, diameter). Their analysis takes the tether itself into account, so direct predicitions for TADRS are not feasable.…”

Section: Tether Orbtial Perturbations Influence Determinator (Topmentioning

confidence: 99%

Influence of orbital perturbations on tethered space systems for active debris removal missions

Becker

Retat

Stoll

2015

AIAA SPACE 2015 Conference and Exposition

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This paper analyses the influence of orbital perturbations on tethered space systems for active debris removal missions in low Earth orbit. Using a flexible (tethered) connection between the chaser satellite and a debris object it is possible to perform an active debris removal mission. For a successful mission, a stabilization and control of the tethered system is necessary. Since the debris object might be non-operational all maneuvers have to be performed by the chaser. Therefore, the development of control laws and equations of motion for the tethered system is indispensable. At the beginning of the development process for control laws it is required to determine the equation of motion of the system and therefore the applied forces. These can be distinguished in active (self-induced: e.g. thruster firing) and passive (foreign-induced: e.g. orbital perturbations) forces. With knowledge of the applied forces, the intensity and expected direction of the movement of the tethered system can be determined. This paper focuses on passive forces that originate from orbital perturbations in the low Earth orbit regime.For this a software tool called "Tether Orbital Perturbations Influence Determinator (TOPID)" is developed. The tool allows to determine the influence of selected orbit perturbations on the tethered space system. The influence is evaluated based on the change in length of the tether between the chaser and the target. In context of the first study five different targets have been selected depending on their criticality to the space debris environment. The influence of the orbital perturbations have been analyzed for the targets.

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Section: Tether Orbtial Perturbations Influence Determinator (Topmentioning

confidence: 99%

Influence of orbital perturbations on tethered space systems for active debris removal missions

Becker

Retat

Stoll

2015

AIAA SPACE 2015 Conference and Exposition

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“…A successful deployment of TSS is the prerequisite for space missions. Much attention has been paid to deployment of TSS and many space experiments were performed in order to investigate the dynamics of TSS and validate the control methods [2,3]. Different kinds of methods were put forward to complete the deployment of TSS.…”

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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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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“…The knowledge of dynamics and simulation of the tethered satellite systems during deployment and retrieval is essential for such a study [1][2][3][4][5]. TSS emerged as a new technology in space-related missions.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of Large Debris Connected to Space Tug by a Tether

Aslanov

Yudintsev

2013

Journal of Guidance, Control, and Dynamics

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A spatial motion of a large passive satellite (space debris) and a space tug connected by an elastic tether is considered. The motion of the system is excited by a thrust force acting on the space tug. Major attention is given to a derivation of the equations of the motion based on the Lagrange formalism. Correctness of the mathematical model is proved by the theorem on variation of angular momentum and by the numerical simulations. The influence of the initial conditions and the system parameters on the behavior of the passive satellite is studied. The possibility of critical modes of the system motion leading to entanglement of the tether is shown by means of the numerical simulations.Nomenclature A, B, C = moments of inertia of the passive satellite, kg · m 2 a, b, c = coordinates of the tether-attachment point in the coordinate frame Sxyz, m c t = tether stiffness, N∕m K H = angular-momentum vector of the system relative to the point T, kg · m 2 ∕s K S = angular-momentum vector of the passive satellite relative to the point S, kg · m 2 ∕s k t = tether-damping coefficient, N · s∕m l = length of the tether, m m H = mass of the space tug, kg m S = mass of the passive satellite (space debris), kg p ψ , p φ = generalized impulses, kg · m 2 ∕s s = distance between centers of mass of the space tug and the passive satellite, m Sxyz = principal coordinate frame of the passive satellite Sx c y c z c = coordinate frame aligned to the line between the center mass of the passive satellite and the center mass of the space tug T = kinetic energy of the system, J ψ, θ, φ = Euler angles that describe attitude motion of the passive satellite relative to the frame Sx c y c z c , rad

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Dynamics of Tethered Space Systems

Cited by 28 publications

References 0 publications

Influence of orbital perturbations on tethered space systems for active debris removal missions

Influence of orbital perturbations on tethered space systems for active debris removal missions

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

Dynamics of Large Debris Connected to Space Tug by a Tether

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