Multi-Objective Non-Fragile Robust Attitude Control for Flexible Microsatellite Close-Proximity Inspection

Li, Yi

doi:10.1109/access.2021.3094044

Cited by 2 publications

(4 citation statements)

References 36 publications

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“…} 𝜔 > 0 is ensured and it can be removed from the left hand side of the inequality (18). It should also be pointed out that when the MRPs approach its boundary 𝜌 𝜎𝑖 , then 𝜆 1𝑖 tends to one and function…”

Section: Remarkmentioning

confidence: 99%

“…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%

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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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Section: Remarkmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

et al. 2022

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“…In order to show the effectiveness of the proposed methods, the disturbance estimation and control performances are verified via numerical simulations. The parameters of servicing spacecraft and non-cooperative target are shown in Table 1 [36]. For the initial values, the vectors r e (0) = [1, −0.5, 0.5] T and e v (0) = [−0.15, 0.1, 0.05] T are selected.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…12 respectively show the control force and torque on position channel and attitude channel, where it can be seen that the maximum force (or torque) in steady-state phase is less than 1.5N (Nm). Meanwhile, the control energy consumption index defined as E = T 0 ∥u∥ 2 dt is also compared with the TSMC proposed in [18], where T is the time interval [36]. The energy consumption is simulated in Fig.…”

Section: Numerical Simulationmentioning

confidence: 99%

Refined Disturbance Rejection-Based Composite Control of Flexible Spacecrafts for Tracking a Tumbling Non-Cooperative Target

et al. 2022

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When tracking a tumbling non-cooperative target, the position and attitude maneuver control with high-precision as well as fast-response performances is required for flexible spacecrafts. However, the unknown rigid-flexible coupling and model uncertainties will degrade the control performances significantly. Therefore, this paper proposes a refined disturbance rejection-based composite control method for spacecraft position and attitude tracking. First of all, the disturbances including the rigid-flexible coupling and model uncertainties are described by an exogenous model by fully using the partially known disturbance information (e.g., modal frequency and damping). Then, a novel exogenous model-based sliding mode disturbance observer (SMDO) is proposed to achieve the refined disturbance estimation. Next, by combining the SMDO in the feedforward loop and an adaptive terminal sliding mode control (ATSMC) in the feedback loop, a finite-time composite control law is proposed to ensure the fast disturbance rejection and position/attitude tracking simultaneously. In the composite controller, a novel nonsingular terminal sliding mode surface with arctangent function is proposed. Moreover, a time-varying boundary Lyapunov function (BLF) is designed to preassign the transient and steady-state performances of sliding mode surface. Finally, the effectiveness of proposed method is verified via numerical simulation.INDEX TERMS Spacecraft position and attitude tracking, tumbling non-cooperative target, rigid-flexible coupling, sliding mode disturbance observer (SMDO), composite control.

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Multi-Objective Non-Fragile Robust Attitude Control for Flexible Microsatellite Close-Proximity Inspection

Cited by 2 publications

References 36 publications

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

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

Refined Disturbance Rejection-Based Composite Control of Flexible Spacecrafts for Tracking a Tumbling Non-Cooperative Target

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