Autonomous spacecraft rendezvous with finite time convergence

He, Shaoming; Lin, Defu; Wang, Jiang

doi:10.1016/j.jfranklin.2015.08.008

Cited by 28 publications

(11 citation statements)

References 36 publications

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“…Obviously, results mentioned above can only achieve asymptotic stability for the spacecraft rendezvous maneuver. In contrast to these asymptotically stable methods, finite-time control methods have much more superior qualities in convergence rate, robustness against disturbance and control accuracy [14]- [16], and leading to wide applications in spacecraft rendezvous maneuver [24]- [27]. In [24], nonsingular terminal sliding mode control technology (NTSMCT) was utilized to solve the control issue for spacecraft rendezvous maneuver by incorporation with a finite-time disturbance observer.…”

Section: Introductionmentioning

confidence: 99%

“…In contrast to these asymptotically stable methods, finite-time control methods have much more superior qualities in convergence rate, robustness against disturbance and control accuracy [14]- [16], and leading to wide applications in spacecraft rendezvous maneuver [24]- [27]. In [24], nonsingular terminal sliding mode control technology (NTSMCT) was utilized to solve the control issue for spacecraft rendezvous maneuver by incorporation with a finite-time disturbance observer. Totally different from the method proposed in [24], a finite-time algorithm was presented in [25] by resorting to the line-of-sight based control strategy.…”

Section: Introductionmentioning

confidence: 99%

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Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

et al. 2020

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This paper investigates the robust finite-time rendezvous maneuver control for spacecraft via sliding mode control technology. Two control architectures are devised for realizing the control objective, where a novel-developed sliding mode surface (SMS) is designed by resorting to the hyperbolic tangent function. Without considering the chattering problem inherent in sliding mode control, a basis control scheme is constructed to force the tracking errors entering a compact set in finite time. To reduce the effect of the chattering phenomenon, a modified controller is established by resorting to the well-designed adaptive laws. Both of these two controllers can ensure finite-time convergence for the entire system. Theoretical analysis and numerical simulations have shown the effectiveness and superiorities of the proposed methods. INDEX TERMS Spacecraft rendezvous maneuver, finite-time control, sliding mode control, chattering problem, adaptive control.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

et al. 2020

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“…[29] provided a nonsingular terminal sliding mode rendezvous law with an extended state observer to estimate the lumped disturbance. By using a linear quadratic optimal control method to acquire the equivalent part, [30] proposed an integral SMC technique base robust guidance law for spacecraft formation flying. Although above SMC rendezvous algorithms can meet the requirements and guarantee the performance of chaser spacecraft in autonomous rendezvous phase, the properly control-gains selection for SMC algorithms is still a difficult problem to overcome.…”

Section: Introductionmentioning

confidence: 99%

Velocity-Free Fault-Tolerant Rendezvous Law Based on Dual-Layer Adaptive Algorithm

Wang

Shi

et al. 2020

IEEE Access

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Considering the scenario that the obstinate and difficult-repaired sensor and actuator failure always occurs during the spacecraft rendezvous guidance phase and may cause terrible performance, this paper studies the fault-tolerant guidance method and proposes a velocity-free guidance algorithm. Above guidance law is based on a dual-layer adaptive multi-variable super-twisting-like algorithm, where two waving gains are introduced to autonomously adjust the system trajectory subject to the relative velocity. Hence, the complex parameter selection problem is overcome. Moreover, to overcome the sensor fault in relative-velocity channel, a robust observer which can drive the velocity error converge to zero in a small finite time is presented. To test the effectiveness and stability of the proposed guidance law, considering actuator faults, second-order dynamics and saturation, numerical simulations including comparisons and Monte-Carlo are carried out and the results demonstrate above properties.

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“…Then a continuous finite-time control scheme using a new form of TSM for rigid robotic manipulators was proposed in [19], which has faster and high-precision in both the reaching and sliding phase compared with the controllers in [16][17][18] . Motivated by the work of [19], many modified TSMs have been applied successfully in spacecraft control [20][21][22][23][24][25]. In comparison with the modified methods in [22][23][24][25] to avoid singularity, the recently developed nonsingular fast terminal sliding mode control (NFTSMC) method in [26], promises fast convergence speed.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fuzzy finite-time control for spacecraft formation with communication delays and changing topologies

Zhang

Liu

et al. 2017

Journal of the Franklin Institute

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Autonomous spacecraft rendezvous with finite time convergence

Cited by 28 publications

References 36 publications

Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

Velocity-Free Fault-Tolerant Rendezvous Law Based on Dual-Layer Adaptive Algorithm

Adaptive fuzzy finite-time control for spacecraft formation with communication delays and changing topologies

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