Method of Deployment of a Space Tethered System Aligned to the Local Vertical

Zakrzhevskii, A. E.

doi:10.1007/s40295-016-0087-z

Cited by 13 publications

(7 citation statements)

References 15 publications

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“…at the instant of termination of the retrieval mode. By analogy with the author's work [5] we will search for this law in the form of a functional series of the seventh order…”

Section: Mathematical Model Of Systemmentioning

confidence: 99%

“…tension T, which can be calculated on each step of integration using the equation (13). One can obtain the value r(t) on each step of integration of the Cauchy problem (5). Its first time derivatives may be determined from (5) after substitution there the expression (7) for ( ) t ϑ and its time derivatives.…”

Section: Scenario Of Tether Retrievalmentioning

confidence: 99%

“…One can obtain the value r(t) on each step of integration of the Cauchy problem (5). Its first time derivatives may be determined from (5) after substitution there the expression (7) for ( ) t ϑ and its time derivatives. As a result, we obtain the expression for the tension force T(t), which may be used at numerical integration of the Cauchy problem for HCW equations with help of the Fortran package, written by the author.…”

Section: Scenario Of Tether Retrievalmentioning

confidence: 99%

“…The method developed by the author in [5] is more preferable from the point of view of maintenance of the desirable properties of terminal conditions of a tether. The method is based on the solution of the inverse problem of mechanics under control of fulfillment of the theorem of change of the angular momentum of a tether under the effect of the gravitational torque.…”

Section: Introductionmentioning

confidence: 99%

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Feed-Forward Control for Retrieval Mode of Space Tethered Systems

Ae¹

2018

Int J Astronaut Aeronautical Eng

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ple and reliable method is the method based on using of the gravitational force field. The main objective of the most scenarios of the tether operating is control of its angular momentum, which defines modes of tether motion. Deployment of a tether at the expense of a jet force is less preferable, since it demands considerable fuel expenditure, and complicates the system essentially. The majority of known methods used for construction of control laws of a state of a space tether are based on attempts to match some control law, allowing solving the problem in view. Thus it appears more often that use of such a control leads to appearance of undesirable effects. So, Kissel's law for deployment or law of exponential deployment result in the tether deployment with alignment to a local vertical with appearance of essential longitudinal oscillations. The author reviews in [5] known to date laws of control applicable for the deployment mode and compares their merits and demerits. The mode of the tether retrieval has its features. One of them is transition in rotational mode at a rapid reeling of

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“…at the instant of termination of the retrieval mode. By analogy with the author's work [5] we will search for this law in the form of a functional series of the seventh order…”

Section: Mathematical Model Of Systemmentioning

confidence: 99%

Section: Scenario Of Tether Retrievalmentioning

confidence: 99%

Section: Scenario Of Tether Retrievalmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Feed-Forward Control for Retrieval Mode of Space Tethered Systems

Ae¹

2018

Int J Astronaut Aeronautical Eng

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“…[11], assume a massless tether, which leads to a very simple set of differential equations and still yields reliable results. In [8] a comparison between the control of the simple model with massless tether and a finite element calculation of a massive tether with the tension force obtained from the simple model is performed and it is This article is dedicated to Prof. Francesco Benedettini. demonstrated, that the control is able to steer the satellite close to the target position in short time.…”

Section: Introductionmentioning

confidence: 99%

Time optimal control for the deployment of a tethered satellite allowing for a massive tether

Steindl

2016

Meccanica

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The time optimal deployment of a satellite from a space ship is studied. In order to take the mass and lateral oscillations of the tether into account, a discretized model of the tether is build. Applying Pontryagin's Maximum Principle a time-optimal deployment from a trivial downhanging configuration close to the space ship to another one farther away is computed. It is found, that the obtained solution displays a difficult switching pattern and during the variation of the initial length different kinds of bifurcations occur, leading to discontinuous variations of the optimal solution candidates.

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Introduction

Sun,

Wu,

et al. 2024

Studies in Systems, Decision and Control

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Method of Deployment of a Space Tethered System Aligned to the Local Vertical

Cited by 13 publications

References 15 publications

Feed-Forward Control for Retrieval Mode of Space Tethered Systems

Feed-Forward Control for Retrieval Mode of Space Tethered Systems

Time optimal control for the deployment of a tethered satellite allowing for a massive tether

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