Mission-function control of tethered satellite/climber system

Kojima, Hirohisa; Fukatsu, Kosei; Trivailo, Pavel M.

doi:10.1016/j.actaastro.2014.10.024

Cited by 32 publications

(7 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…and in accordance with equations (10), (11), (12), and (13), the controller input can be constructed as…”

Section: Integral Sliding Mode Controller Designmentioning

confidence: 99%

“…The analytical deployment control law on account of J 2 perturbation, air drag force, and solar pressure was proposed by Yu et al, 10 which presented the necessary and sufficient conditions of parameter domains for tensile state of space tether. Mission function based feedback control is specified for the control problem of the TSS, and Kojima et al 11 developed the mission function by considering the difference in original model. Optimal control is a comprehensive method by viewing the deployment process as a nonlinear optimization problem, where the constrained tension was designed as the terminal condition and the underactuated dynamics can be evaluated by a cost function indirectly, and it has hence been thought of as one of the most highly effective solutions.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Fractional-order sliding mode control for deployment of tethered spacecraft system

Zhu

Sun

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

This paper proposes a fractional-order integral sliding mode control with the order 0 < ν < 1 to stabilize the deployment of tethered spacecraft system with only tension regulation. The work in this paper is partially based on integer-order nonlinear sliding mode controller and improves its performance with fractional-order calculus. The proposed scheme makes use of integral sliding surface to obtain smaller convergence regions of state errors, and the fractional derivative is synthesized to enhance the flexibility of controller design by fining parameters for better dynamic and steady-state performance. Fractional-order observers help to eliminate external disturbances while the adaptive law is presented to remove the adverse effect in stability analyses, and fractional-order uniform ultimate boundedness is proved to guarantee the existence of the proposed sliding surface. According to theoretical analyses, the fractional order will indeed affect the dynamic and steady-state performance of control system, and the proposed method will be verified in numerical simulations compared with the nonlinear sliding mode counterpart.

show abstract

“…and in accordance with equations (10), (11), (12), and (13), the controller input can be constructed as…”

Section: Integral Sliding Mode Controller Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Fractional-order sliding mode control for deployment of tethered spacecraft system

Zhu

Sun

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…The derivation of Eq. (8a) finally leads to a quadratic programming problem to find a programming vector Z ¼ δx T 0 δx T 1 … δx T n δυ 0 δυ 1 … δυ n δυ 0:5 δυ 1:5 … δυ nÀ0:5 ÂÃ T , which minimizes the cost function: 11) subject to.…”

Section: Closed-loop Optimal Control For Tracking Open-loop Optimal Smentioning

confidence: 99%

“…The study shows that to eliminate the inplane oscillations by reversing the direction of the elevator is possible. Kojima et al [11] extended the mission function control method to eliminate the libration motion of a three body tethered system. The proposed method is effective when the total tether length is fixed and the maximum speed of the climber no more than 10 m/s.…”

Section: Introductionmentioning

confidence: 99%

Piecewise Parallel Optimal Algorithm

Zhu¹,

Shi²

2018

Optimization Algorithms - Examples

View full text Add to dashboard Cite

This chapter studies a new optimal algorithm that can be implemented in a piecewise parallel manner onboard spacecraft, where the capacity of onboard computers is limited. The proposed algorithm contains two phases. The predicting phase deals with the openloop state trajectory optimization with simplified system model and evenly discretized time interval of the state trajectory. The tracking phase concerns the closed-loop optimal tracking control for the optimal reference trajectory with full system model subject to real space perturbations. The finite receding horizon control method is used in the tracking program. The optimal control problems in both programs are solved by a direct collocation method based on the discretized Hermite-Simpson method with coincident nodes. By considering the convergence of system error, the current closed-loop control tracking interval and next open-loop control predicting interval are processed simultaneously. Two cases are simulated with the proposed algorithm to validate the effectiveness of proposed algorithm. The numerical results show that the proposed parallel optimal algorithm is very effective in dealing with the optimal control problems for complex nonlinear dynamic systems in aerospace engineering area.

show abstract

“…1 Many international space institutes have launched respective experimental TSS projects, such as TSS-1R, 2 YES2, MAST and SEDS, 3 and have validated the feasibility of TSS in practice. In recent decades, TSS has became a hot issue of space researches, and has been frequently used as the reasonable solutions to space scientific missions, such as formation flight of satellites, 4 safety flight, 5 deorbit of the load, 6,7 space target capture, 8–10 space elevator 11 and space debris removal 12,13 due to flexible configuration, low power consumption and cyclic utilization.…”

Section: Introductionmentioning

confidence: 99%

Pure-tension non-linear sliding mode control for deployment of tethered satellite system

Sun

Cheng

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

This paper presents a sliding mode controller for the deployment of two-body tethered satellite system. A sliding surface design for underactuated system is employed to reconcile pure-tension control scheme with non-linear coupled deployment dynamics. The proposed sliding surface is strictly non-linear. Hence, the control scheme does not require linearization operation of tethered satellite system and can guarantee that all the system states converge to zero with arbitrary small errors. To deal with input constraint of pure-tension control, an adaption is introduced into the controller design to remove the negative effect caused by input constraint in stability analyses and ensures the feasibility of the proposed controller even though command input overtakes the tolerance of tension actuator. To avoid the chattering phenomena, the trivial sign function is removed from the switching input and replaced by the disturbance observer. Numerical results demonstrate the effectiveness of the proposed controller for the deployment of the tethered satellite system.

show abstract

Mission-function control of tethered satellite/climber system

Cited by 32 publications

References 28 publications

Fractional-order sliding mode control for deployment of tethered spacecraft system

Fractional-order sliding mode control for deployment of tethered spacecraft system

Piecewise Parallel Optimal Algorithm

Pure-tension non-linear sliding mode control for deployment of tethered satellite system

Contact Info

Product

Resources

About