Stability analysis of in-plane and out-of-plane periodic motions of electrodynamic tether system in inclined elliptic orbit

Kojima, Hirohisa; Sugimoto, Tetsuro

doi:10.1016/j.actaastro.2009.02.006

Cited by 43 publications

(14 citation statements)

References 25 publications

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“…Kojima et al proposed to control the librational motion of a three-mass TSS in an elliptic orbit by using the existing delayed feedback control [53], and designed an innovative control scheme by combining the delayed feedback control with model-following and decoupling-control method, to improve the control performance. In the next paper, Kojima with Sugimoto used the feedback delayed method to demonstrate the stability of in-plane and out-plane periodic motions of EDT in an inclined elliptic orbit [79].…”

Section: Delayed Feedback Control Methodsmentioning

confidence: 99%

Review of Control Methods and Strategies of Space Tether Satellites

Tirop¹,

Zhang²

2019

AJTTE

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Space tether satellites systems are one of the most promising directions in the modern space industry. Such systems consist of two or more spacecraft connected to each other by very long tethers. Great extension and variable configuration of the system in the orbital flight conditions provide some dynamic features, which are not typical of conventional spacecraft. The concept of the tethered satellite system (TSS) promises to revolutionize many aspects of space exploration and exploitation. It provides not only numerous possible and valuable applications, but also challenging and interesting problems related to their dynamics, control, and physical implementation. The overarching theme of the paper is to show various control methods of the tethered satellites system (TSS) that have been undertaken recently, and also to emphasize on the importance of the TSS control method as an important aspect in the tether concepts, design, and missions. This review article presents the historical background and recent hot topics for the space tethers, and introduces the dynamics and control of TSSs in a progressive manner, from basic operating principles to the state-of-the-art achievements. The paper introduces the strategies and methods applied in controlling the TSS not excluding their advantages and disadvantages during the tether satellite deployment, retrieval, and station keeping procedures. At the end of the paper, a conclusion is made about the effectiveness of the control methods in stabilizing the libration and vibration motions of the TSS.

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Section: Delayed Feedback Control Methodsmentioning

confidence: 99%

Review of Control Methods and Strategies of Space Tether Satellites

Tirop¹,

Zhang²

2019

AJTTE

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“…Therefore, it is assumed that the orbits are frozen no matter how the Lorentz force acts on the system. Based on the assumptions of frozen orbit and ignoring Earth's rotation, Q and Q in equation (15) are periodic.…”

Section: Libration Dynamic Equation Of Edtmentioning

confidence: 99%

“…In˜arrea et al 14 employed the software package AUTO2007 to obtain the periodic solutions for the system, and stabilized the unstable periodic solution using time-delay feedback control methods. Kojima and Sugimoto 15 analyzed the stability of in-plane/out-of-plane periodic motions of EDT in an elliptical and inclined orbit. In addition, Kojima and Sugimoto 16 proposed a switching delayed feedback control method to stabilize the librational in-plane/out-of-plane periodic motion of EDT.…”

Section: Introductionmentioning

confidence: 99%

Periodic solutions and stability analysis of electrodynamic tethers for 13 degree international geomagnetic reference field

Yang

Cai

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The geomagnetic field plays a crucial role in the operation of the electrodynamic tether system in the space. Using the 13 degree International Geomagnetic Reference Field to model the geomagnetic field, the libration dynamic equation of the system is established. The nonlinear libration dynamic equation of the system is a typical chaotic system. In the dynamic equation, there are four free parameters: the orbital inclination, the orbital eccentricity, the altitude of the perigee and the electrodynamic parameter. After adding dummy control terms into the dynamic system, the extended time delayed autosynchronization control method is employed to calculate the periodic solutions of the dynamic equation. The shapes and amplitudes of the periodic libration motions change with the free parameters regularity. Based on the Floquet theory, the stabilities of the periodic solutions are analyzed. The orbit time during which the initial periodic libration turns to the rotation motion is defined as the failure time. It is used to measure the instability of the periodic solution and validate the results from the Floquet theory. Simulations show that the results from the failure time are consistent with the results from the Floquet theory. For all parameters, the periodic solutions are all unstable. In addition, the relationships between the instabilities of the periodic solutions and the free parameters are obtained.

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“…Due to recent guidelines on the deorbiting of LEO satellites at their end of life by the Inter-Agency Space Debris Coordination Committee (IADC) [1], the attention of governments, space agencies and researchers on this issue has grown worldwide in the last years [2][3][4][5]. Several concepts are under study to provide new alternatives to carry out deorbiting maneuvers in a low-cost, safe and reliable way (Ref.…”

Section: Introductionmentioning

confidence: 99%

Two-bar model for free vibrations damping of space tethers by means of spring-dashpot devices

et al. 2014

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Present guidelines indicate the need to deorbit new satellites launched into low Earth orbit (LEO) within 25 years from their end of life. Our research task is to develop a new technology suitable to deorbit a satellite at the end of life with as small an impact as possible on the mass budget of the mission. An alternative to the traditional chemical rockets consists in using an electrodynamic tether that, through its interaction with the Earth ionosphere and magnetic field, can take advantage of Lorentz forces for deorbiting purposes. However, Lorentz forces produce a low and yet continuous injection of energy into the system that, in the long run, can bring the tether to instability. This paper addresses this issue through the analysis of the benefits provided by an elastic-viscous damping device installed at the attachment point of the tether to the spacecraft. The analysis carried out by means of linearization of dynamics equations and numerical simulations show that a well-tuned damper can efficiently absorb the kinetic energy from the tether thus providing system stability during deorbiting. @ CEAS 201

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Stability analysis of in-plane and out-of-plane periodic motions of electrodynamic tether system in inclined elliptic orbit

Cited by 43 publications

References 25 publications

Review of Control Methods and Strategies of Space Tether Satellites

Review of Control Methods and Strategies of Space Tether Satellites

Periodic solutions and stability analysis of electrodynamic tethers for 13 degree international geomagnetic reference field

Two-bar model for free vibrations damping of space tethers by means of spring-dashpot devices

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