Extension of tethered satellites in the atmosphere

Pradeep, S.; Kumar, K.

doi:10.1016/s0094-5765(02)00121-2

Cited by 7 publications

(5 citation statements)

References 7 publications

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“…Instead of an additional movable mass, tether tension and thrusters can be used to control the tether swing. 12,13) However, any movable mass on the tether and thrusters obviously results in an increase in the mass of the TSS. In a previous study, 14) linear feedback of the tether length and tether length rate of change was shown to be sufficient to guarantee the asymptotic stability of a closed-loop system to a desired equilibrium point under the assumption of no mass and a non-flexible tether.…”

Section: Nomenclaturementioning

confidence: 99%

“…As a candidate solution to overcome the above problems, in this paper, we consider an LQR-based control method cooperating with a pole assignment shift technique 15) to make the controller more robust to perturbations than a simple LQR-based controller. In addition, in contrast to a previous study, 13) in which the tether tension and thruster were assumed as control inputs, in this paper, we assume tether deployment control without a thruster. Furthermore, we intend to verify the validity of the controller not only numerically, but also experimentally using a ground-based TSS motion emulator, [16][17][18] in which the slope inclination angle is changed to emulate the gravity gradient affecting the subsatellite as much as possible.…”

Section: Nomenclaturementioning

confidence: 99%

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Deployment Control of a Tethered Satellite System for Rendezvous with a Target

Kojima

Taruoka

2016

Trans. Japan Soc. Aero. S Sci.

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This paper considers deployment control of a tethered satellite system (TSS) for rendezvousing a subsatellite with a target object orbiting at a lower altitude. Contrary to past studies that considered a linear quadratic regulator (LQR), in the present study, an LQR-based controller is designed using a pole assignment shift technique, in which the acceleration of the tether deployment or retrieval is treated as the control input and no propellant is used. For simplicity, the TSS is represented as a dumbbell model. The tether tension is calculated based on the tether state variables (tether length, tether length rate, tether angle, tether angle rate, and acceleration of the tether deployment treated as the control input) in order to confirm whether or not tether slack occurs. The experimental results show that the proposed control law contributes to reducing the difference between the desired and experimental tether librational motions.

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Section: Nomenclaturementioning

confidence: 99%

Section: Nomenclaturementioning

confidence: 99%

Deployment Control of a Tethered Satellite System for Rendezvous with a Target

Kojima

Taruoka

2016

Trans. Japan Soc. Aero. S Sci.

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“…In another study, interorbital rendezvous with small relative inclination was also analyzed, and a nonlinear receding horizon controller was considered for tracking highly nonlinear systems by producing disturbances in system mass distributions and perturbations to initial system conditions [ 22 ]. Pradeep and Kumar [ 23 ] proposed nonlinear feedback tension control laws based on Liapunov’s method, used a linear state variable feedback control and affirmed the desired length of extended tethers in a reasonable amount of time.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Behavior Analysis and Stability Control of Tethered Satellite Formation Deployment

Zhang

et al. 2021

Sensors

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In recent years, Tethered Space Systems (TSSs) have received significant attention in aerospace research as a result of their significant advantages: dexterousness, long life cycles and fuel-less engines. However, configurational conversion processes of tethered satellite formation systems in a complex space environment are essentially unstable. Due to their structural peculiarities and the special environment in outer space, TSS vibrations are easily produced. These types of vibrations are extremely harmful to spacecraft. Hence, the nonlinear dynamic behavior of systems based on a simplified rigid-rod tether model is analyzed in this paper. Two stability control laws for tether release rate and tether tension are proposed in order to control tether length variation. In addition, periodic stability of time-varying control systems after deployment is analyzed by using Floquet theory, and small parameter domains of systems in asymptotically stable states are obtained. Numerical simulations show that proposed tether tension controls can suppress in-plane and out-of-plane librations of rigid tethered satellites, while spacecraft and tether stability control goals can be achieved. Most importantly, this paper provides tether release rate and tether tension control laws for suppressing wide-ranging TSS vibrations that are valuable for improving TSS attitude control accuracy and performance, specifically for TSSs that are operating in low-eccentricity orbits.

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“…14–16 Besides, some researchers studied the dynamics model in the presence of aerodynamic forces, which shows some more complicated dynamics characteristics compared to the case that aerodynamic forces are neglected. 17–19…”

Section: Introductionmentioning

confidence: 99%

Dynamics modeling and model selection of space debris removal via the Tethered Space Robot

Zhang

Huang

Meng

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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This work proposes a scheme to select a proper dynamics model for space debris removal which is captured by a Tethered Space Robot. A proper dynamics model is crucial for the parameters estimation and controller design in a Tethered Space Robot mission, in particular, for the retrieval or de-orbiting of uncooperative target. A new dynamics model of the system is derived by treating the base satellite and the space debris as rigid bodies in the presence of offsets, and with the effect of the tether’s flexibility and elasticity. Then the equations of motion are simplified based on the attitude analysis and numerical simulations in different cases. It is concluded that in the Tethered Space Robot’s mission, the strong coupled attitude motions among the base, target satellites, and the tether cannot be ignored during the retrieval, which is totally different from the traditional tethered satellite system. The attitude motions of the system in different conditions are discussed respectively, and a method of the model selection of the system during post-capture and retrieval/de-orbiting phase is proposed, which is a balance of the accuracy and facility. Finally, a control scheme is used to prove this conclusion.

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Extension of tethered satellites in the atmosphere

Cited by 7 publications

References 7 publications

Deployment Control of a Tethered Satellite System for Rendezvous with a Target

Deployment Control of a Tethered Satellite System for Rendezvous with a Target

Dynamic Behavior Analysis and Stability Control of Tethered Satellite Formation Deployment

Dynamics modeling and model selection of space debris removal via the Tethered Space Robot

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