Dynamics of variable-length tethers with application to tethered satellite deployment

Tang, Jiakui; Ren, Guang-Kun; Zhu, W. D.; Ren, Hsuan

doi:10.1016/j.cnsns.2010.11.026

Cited by 70 publications

(32 citation statements)

References 30 publications

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“…In the dynamic equations (11) to (16), environmental force F e including aerodynamic drag F a and solar pressure F s is taken into account 5,20…”

Section: Dynamic Characters In Deploymentmentioning

confidence: 99%

“…9 Dynamic models taking the tether as series of elements with lumped masses or as variable-length element are further developed to describe the variable-length tether in the deployment and retrieval processes. 10,11 Control strategies, based on more or less complex models, are proposed to regulate the tether swing along proposed direction during deployment, retrieval, and station-keeping. Control action can be implemented by modulating tether tension, [12][13][14][15] tether length, or length rate, [16][17][18][19][20][21] by applying thrusters, [22][23][24] or by moving an actuator mass along the tether.…”

Section: Introductionmentioning

confidence: 99%

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Attitude dynamics and thrust control for short tethered sub-satellite in deployment

Liu

Zhou

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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Dynamic characters and control strategy for short tethered satellite system in deployment are studied in this paper. Tether elastic oscillation and sub-satellite attitude motion are considered in the dynamic model. Sub-satellite releasing method with an initial velocity and a negative acceleration is proposed for fast deployment. It is indicated that the short dimension and fast deployment make dynamic characteristics of both the tether and the sub-satellite different from those of the long-tether systems. Control strategy is designed based on these dynamic characters. Thrusters are considered to provide active control for the tether and the attitude of the sub-satellite. Variable structure control is adopted, taking into account the nonlinear dynamics of the system and the on-off output of the thrusters. Numerical simulation shows that the tethered sub-satellite can be deployed to designed direction in or out of the orbit plane with thrust control. The tension of the tether is positive during deployment. The in-plane angle of the tether is controlled within 0.1 . The out-of-plane angle passively keeps near its initial releasing value. In addition, the attitude angles of the sub-satellite are controlled or passively remain within 0.5 . This fast deployment provides flexibility for tether assisted space operations.

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“…In the dynamic equations (11) to (16), environmental force F e including aerodynamic drag F a and solar pressure F s is taken into account 5,20…”

Section: Dynamic Characters In Deploymentmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Attitude dynamics and thrust control for short tethered sub-satellite in deployment

Liu

Zhou

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…They found that the numerical results obtained using the finite segment method agree well with the results obtained using the experiment. Tang et al [25] studied the dynamics of the variable-length satellite tethers using flexible multibody theory based on the absolute nodal coordinate formulation. The dynamics of deploying a slender continuum have also been modeled in the context of what is known as the reverse spaghetti problem [24,26].…”

Section: Introductionmentioning

confidence: 99%

Energetics and Invariants of Axially Deploying Beam with Uniform Velocity

2016

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“…The former is the finite element model and the latter is the most popular bead model. [17][18][19]26,27] In this model, the tether mass elasticity and flexibility are all considered. The tether is more realistically represented by increasing the element number.…”

Section: Description Of Tsrmentioning

confidence: 99%

An Effective Approach Control Scheme for the Tethered Space Robot System

Meng

Huang

2014

International Journal of Advanced Robotic Systems

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The tethered space robot system (TSR), which is composed of a platform, a gripper and a space tether, has great potential in future space missions. Given the relative motion among the platform, tether, gripper and the target, an integrated approach model is derived. Then, a novel coordinated approach control scheme is presented, in which the tether tension, thrusters and the reaction wheel are all utilized. It contains the open-loop trajectory optimization, the feedback trajectory control and attitude control. The numerical simulation results show that the rendezvous between TSR and the target can be realized by the proposed coordinated control scheme, and the propellant consumption is efficiently reduced. Moreover, the control scheme performs well in the presence of the initial state's perturbations, actuator characteristics and sensor errors.

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Dynamics of variable-length tethers with application to tethered satellite deployment

Cited by 70 publications

References 30 publications

Attitude dynamics and thrust control for short tethered sub-satellite in deployment

Attitude dynamics and thrust control for short tethered sub-satellite in deployment

Energetics and Invariants of Axially Deploying Beam with Uniform Velocity

An Effective Approach Control Scheme for the Tethered Space Robot System

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