Disturbance-Observer-Based Robust Backstepping Attitude Stabilization of Spacecraft Under Input Saturation and Measurement Uncertainty

Sun, Liang; Zheng, Zewei

doi:10.1109/tie.2017.2694349

Cited by 168 publications

(71 citation statements)

References 49 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…, n f , satisfy the constraints in (10). Our LMI-based approach for the design of a stabilizing control law u, which will be designed in the sequel, can be applied for a general class of fully nonlinear systems such as (hyper) chaotic systems as in [59,60], robotic/mechatronic systems as in [43,46], and underactuated mechanical systems [61,62], just to mention a few. us, the nonlinearity term, saying…”

Section: Class Of Nonlinear Systemsmentioning

confidence: 99%

“…e design of controllers for continuous-time and discrete-time systems by taking into consideration the actuator saturation has been extensively studied in the past few decades [17][18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36]. Some works have investigated the problem of uncertainties and actuator saturation in mechatronic systems such as the vehicle lateral dynamics [37], the vehicle active suspension systems [38][39][40][41], the rigid spacecraft [42,43], the inertia wheel inverted pendulum [12], the supercavitating vehicle [44], the flexible robotic manipulator [45], and the marine surface vessel [46], among others. e concept of attractive invariant sets has been generally proposed for linear systems involving actuator saturation [5,20,28,29,36,44,[47][48][49][50][51].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

LMI-Based Robust Stabilization of a Class of Input-Constrained Uncertain Nonlinear Systems with Application to a Helicopter Model

Gritli

2020

Complexity

View full text Add to dashboard Cite

This paper is concerned with the robust stabilization of a class of continuous-time nonlinear systems, with an application to the pitch dynamics of a simple helicopter model, via an affine state-feedback control law using the linear matrix inequality (LMI) approach. The nonlinear dynamics is subject to norm-bounded parametric uncertainties and disturbances. In addition, the problem of actuator nonlinearity is addressed by considering the saturation effect of the control law. We demonstrate first that the synthesis problem of the saturated controller is expressed in terms of bilinear matrix inequalities (BMIs). Thanks to the Schur complement lemma and the matrix inversion lemma, we convert these BMIs into LMIs allowing the simultaneous computation of the two gains of the affine controller. Furthermore, we address in this work the estimation problem of the domain of attraction using the invariant set concept. This is solved by computing the largest attractive invariant ellipsoid. Compared with previous works, the research procedure of such ellipsoidal set is achieved in a single step with a reduced number of LMI constraints and then with less conservative conditions. A portfolio of numerical results is presented. The effectiveness and robustness of the proposed saturated controller in the stabilization of the adopted helicopter pitch model toward parametric uncertainties and disturbances are illustrated through simulation results.

show abstract

Section: Class Of Nonlinear Systemsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

LMI-Based Robust Stabilization of a Class of Input-Constrained Uncertain Nonlinear Systems with Application to a Helicopter Model

Gritli

2020

Complexity

View full text Add to dashboard Cite

show abstract

“…With the improvement of space technology, higher attitude control requirements are necessary in the space flight mission design and achievement . However, in practice, the existence of uncertainties and external disturbances makes it difficult to achieve the attitude control with rapid convergence and high accuracy, simultaneously.…”

Section: Introductionmentioning

confidence: 99%

“…With the improvement of space technology, higher attitude control requirements are necessary in the space flight mission design and achievement. [1][2][3][4][5][6][7][8][9][10][11][12][13][14] However, in practice, the existence of uncertainties and external disturbances makes it difficult to achieve the attitude control with rapid convergence and high accuracy, simultaneously. Due to the good performance of finite-time convergence and widely robustness, finite-time control schemes have been gradually implemented in spacecraft attitude control.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Tao

Chen

et al. 2019

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

Summary In this paper, an adaptive fixed‐time fault‐tolerant control scheme is presented for rigid spacecraft with inertia uncertainties and external disturbances. By using an inverse trigonometric function, a novel double power reaching law is constructed to speed up the state stabilization and reduce the chattering phenomenon simultaneously. Then, an adaptive fixed‐time fault‐tolerant controller is developed for the spacecraft with the actuator faults, such that the fixed‐time convergence of the attitude and angular velocity could be guaranteed, and no prior knowledge on the upper bound of the lumped uncertainties is required anymore in the controller design. Comparative simulations are provided to illustrate the effectiveness and superior performance of the proposed scheme.

show abstract

“…Attitude stabilization is an active research direction [12][13][14][15], and is also the core part of MSTA. The diagram of the attitude stabilization system is shown in this part.…”

Section: Introduction Of Attitude Stabilization Systemmentioning

confidence: 99%

Design and Implementation of Attitude Stabilization System for Marine Satellite Tracking Antenna

et al. 2018

View full text Add to dashboard Cite

Marine Satellite Tracking Antenna (MSTA) is an important shipboard device for ships to bidirectionally communicate with the outside. The attitude stabilization system is an important part of MSTA for keeping the antenna dish tracking the geostationary satellite in the presence of severe ship dynamics. In this paper, the designed high-performance attitude stabilization system is introduced, including hardware system, model identification and controller design. The detailed procedure for identifying the stepper motor model is stated, which is different from conventional procedure. The design procedure of the robust controller based on H ∞ loop shaping is given. The designed attitude stabilization system was tested on a Stewart platform that was used as the ship simulator. From the testing results, it can be seen that the performance of designed attitude stabilization system is very high and the tracking angle error can be limited to within ± 0.15 deg, which satisfies the performance requirements of Ka-band MSTA product.

show abstract

Disturbance-Observer-Based Robust Backstepping Attitude Stabilization of Spacecraft Under Input Saturation and Measurement Uncertainty

Cited by 168 publications

References 49 publications

LMI-Based Robust Stabilization of a Class of Input-Constrained Uncertain Nonlinear Systems with Application to a Helicopter Model

LMI-Based Robust Stabilization of a Class of Input-Constrained Uncertain Nonlinear Systems with Application to a Helicopter Model

Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Design and Implementation of Attitude Stabilization System for Marine Satellite Tracking Antenna

Contact Info

Product

Resources

About