Coupled orbit-attitude dynamics and trajectory tracking control for spacecraft electromagnetic docking

Shi, Keke; Liu, Chuang; Sun, Zhiyong; Yue, Xiaokui

doi:10.1016/j.apm.2021.08.030

Cited by 55 publications

(41 citation statements)

References 24 publications

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“…By choosing smaller intervals for 𝑒 and 𝑒, the overshoot and error are decreased and the error signal converges to zero more quickly. The proposed approach is compared to the classic fast terminal sliding mode control (CFTSMC) method [39] and classic sliding mode control (CSMC) [21,40], which considers the control of spacecraft electromagnetic docking and DC servo motor. The dynamics of the sliding surfaces for all three approaches are depicted in Figure 3.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…(CFTSMC) method [39] and classic sliding mode control (CSMC) [21,40], which considers the control of spacecraft electromagnetic docking and DC servo motor. The dynamics of the sliding surfaces for all three approaches are depicted in Figure 3.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…An FTSMC approach was considered for the multi-input multi-output twin-rotor system in [20]. In [21], by using the fixed-time disturbance observer, the tracking control of aircraft with external disturbances and measuring noises was investigated; however, the suggested method [21] did not provide a law to adjust the switching control gains and improve the system's dynamic response. The study reported in [22] showed that combining the FTSMC with a fuzzy logic approach to adjust the sliding surface and switching control gains can further improve the system's dynamic response.…”

Section: Introductionmentioning

confidence: 99%

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Design of an LMI-Based Fuzzy Fast Terminal Sliding Mode Control Approach for Uncertain MIMO Systems

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This paper proposes a linear matrix inequality (LMI)-based fuzzy fast terminal sliding mode control (FFTSM) approach for a multi-input multi-output (MIMO) system. This design aims to achieve the finite-time convergence of system trajectories to their desired values, while at the same time eliminating the chattering problem. Finite-time stability is proven using the Lyapunov theory and the control parameters are obtained using the LMI approach. The fuzzy logic approach is considered to fine tune the controller parameters and reduce the tracking error and control signal amplitude. The performance of the proposed approach is assessed using a simulation study of a direct current (DC) motor. The obtained results confirm the effectiveness of the proposed control design. Simplicity of the design, robustness, finite-time convergence, and chattering-free dynamics are among the features of the proposed approach.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Design of an LMI-Based Fuzzy Fast Terminal Sliding Mode Control Approach for Uncertain MIMO Systems

Mokhtare

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et al. 2022

Mathematics

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“…For these reasons, achieving high accuracy attitude control for spacecraft system has become a challenging problem. Over the past few years, the demanding issue of spacecraft attitude control has attracted profound attention and numerous control laws are available; for instance, backstepping method [9], eventtriggered control [10,11], model predictive control (MPC) [12,13], sliding mode control (SMC) [14][15][16][17], non-fragile output-feedback control [18,19], adaptive control [20], fuzzy control [21], fault-tolerant control [22], disturbance observer-based control [23][24][25][26][27], etc.…”

Section: Introductionmentioning

confidence: 99%

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

et al. 2022

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The problem of attitude control for rigid spacecraft under the attitude and angular velocity constraints is investigated in this study. Particularly, a simple structure constrained proportional-derivative (PD)-like control is proposed which contains two portions. The first portion is a conventional PD control to provide convergence of the system states; whereas the second portion provides the desired performance specifications such as convergence rate, overshoot and steady-state bound for attitude and rotation velocity to improve the attitude pointing accuracy and pointing stability. The distinctive property of the suggested constrained control method is to ensure the desired performance in transient and steady-state phases for all the system states. It also possesses much simpler structure compared to the existing constrained control techniques since it is based on a new methodology. The simulation results conducted on a rigid spacecraft verify the efficiency of the proposed approach.

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“…However, other novel space control methods, such as electromagnetic docking [36,37], may receive little benefit from the presented setup. The electromagnetic docking technique involves a set of small spacecraft performing proximity operations that can mutually influence their pose using the homonymous forces.…”

Section: Introductionmentioning

confidence: 99%

A Concurrent Testing Facility Approach to Validate Small Satellite Combined Operations

et al. 2021

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Federated remote laboratories allow for the execution of experiments ex situ. The coordination of several laboratories can be used to perform concurrent experiments of combined space operations. However, the latency of the communications between facilities is critical to performing adequate real-time experiments. This paper presents an approach for conducting coordinated experiments between floating platforms at two remote laboratories. Two independently designed platforms, one at Luleå University of Technology and the other at La Sapienza University of Rome, were established for this purpose. A synchronization method based on the Simple Network Time Protocol was created, allowing the offset and delay between the agents to be measured.Both platforms exchange data about their measured time and pose through a UDP/IP protocol over the internet. This approach was validated with the execution of simulated operations. A first demonstrative experiment was also performed showing the possibility to realize leader/follower coordinated operations. The results of the simulations and experiments showed communication delays on the order of tens of milliseconds with no significant impact on the control performance. Consequently, the suggested protocol was proven to be adequate for conducting coordinated experiments in real time between remote laboratories.

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Coupled orbit-attitude dynamics and trajectory tracking control for spacecraft electromagnetic docking

Cited by 55 publications

References 24 publications

Design of an LMI-Based Fuzzy Fast Terminal Sliding Mode Control Approach for Uncertain MIMO Systems

Design of an LMI-Based Fuzzy Fast Terminal Sliding Mode Control Approach for Uncertain MIMO Systems

A Low-Complexity PD-Like Attitude Control for Spacecraft With Full-State Constraints

A Concurrent Testing Facility Approach to Validate Small Satellite Combined Operations

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