Dynamic propagation of space tether system motion

Zanardi, Maria Cecília; Livio, B.; Prado, P. R.; Silva, William Reis; Baroni, Leandro

doi:10.1088/1742-6596/1365/1/012006

Cited by 1 publication

(4 citation statements)

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“…This tether can be expanded or retracted, making a T tension arise in the wire. A similar STS was discussed by Denney and Greene (1991), Yong et al (2009) and Zanardi et al (2019). The equations that describe the translational and rotational motion of the subsatellite around the main satellite are presented in Denney and Greene (1991).…”

Section: Introductionmentioning

confidence: 83%

“…In this paper, an STS composed of two satellites was considered (Zanardi et al 2019), a main satellite S 1 with mass m 1 and a subsatellite S 2 , with mass m 2 , as illustrated in Fig. 1.…”

Section: Introductionmentioning

confidence: 99%

“…The results of dynamic propagation associated with the motion of the subsatellite around the main satellite are shown in Zanardi et al (2019). A 4 th Order Runge-Kutta method was used for the integration, with the MATLAB software.…”

Section: Introductionmentioning

confidence: 99%

“…It has been identified that the subsatellite has a counterclockwise precession movement in the orbital plane of the main satellite and that it oscillates vertically through this movement. The integration methods developed by Zanardi et al (2019) are useful for the control process used in this paper.…”

Section: Introductionmentioning

confidence: 99%

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Control for the Space Tether System Motion

Zanardi

Prado

Baroni

2020

J.Aerosp. Technol. Manag.

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This paper proposed a study of a spatial tether system (STS), composed by two satellite (a main satellite and a subsatellite), with the objective of developing a control system in which the motion of the subsatellite is limited in the orbital plane of the main satellite. The linear quadratic regulator (LQR) method is used to implement this control, which is an optimal control with state feedback to predict the linearization of the equations of motion to calculate the feedback gain, using the resolution of Riccati equation. The results show an effective control, with the motion of the subsatellite limited only to the stretch of the cable that links both satellites. However, it is necessary to introduce an auxiliary torque, since the linearized equation associated with the second variation of the angle out of the plan does not have a term independent of the state vector.

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Section: Introductionmentioning

confidence: 83%

“…In this paper, an STS composed of two satellites was considered (Zanardi et al 2019), a main satellite S 1 with mass m 1 and a subsatellite S 2 , with mass m 2 , as illustrated in Fig. 1.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations