Attitude controller for reentry vehicles using state-dependent Riccati equation method

Daocheng, Xie; Wang, Zhongwei; Zhang, Weihua

doi:10.1007/s11771-013-1684-7

Cited by 7 publications

(2 citation statements)

References 7 publications

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“…In the past few years, some linear and nonlinear control methods such as gain scheduling , dynamic inversion , trajectory linearization control , state‐dependent Riccati equation , Theta‐D control , and backstepping control have been carried out on reentry attitude control, and many approaches have acquired great development in this respect. Although these control methods mentioned earlier yield the possibility of attitude tracking for reentry RLV, sliding mode control is still the main choice when one needs to deal with a nonlinear system with uncertainties and external disturbances more effectively .…”

Section: Introductionmentioning

confidence: 99%

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Dong

Zong

Tian

et al. 2016

Int. J. Robust. Nonlinear Control

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Summary Reusable launch vehicle (RLV) should be under control in the presence of model uncertainty and external disturbance, which is considered as torque perturbation in this paper during the reentry phase. Such a challenge imposes tight requirements to the enhanced robustness and accuracy of the vehicle autopilot. The key of this paper is to propose an adaptive‐gain multivariable super‐twisting sliding mode controller when considering that the bounds of uncertainty and perturbation are not known. The important features of the controller are that the adaptation algorithm can achieve non‐overestimating values of the control gains and the multivariable super‐twisting sliding mode approach can obtain a more elegant solution in finite time. According to the multiple‐time scale features, the dynamics of RLV attitude motion are divided into outer‐loop subsystem and inner‐loop subsystem. On this basis, the controllers are designed respectively to ensure the finite‐time reentry attitude tracking. In addition, a proof of the finite‐time convergence for the overall system is derived using the Lyapunov function technique and multiple‐time scale characteristic. Finally, simulation results of six degree‐of‐freedom RLV are provided to verify the effectiveness and robustness of the proposed controller in tracking the guidance commands as well as achieving a safe and stable reentry flight. Copyright © 2016 John Wiley & Sons, Ltd.

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Section: Introductionmentioning

confidence: 99%

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Dong

Zong

Tian

et al. 2016

Int. J. Robust. Nonlinear Control

View full text Add to dashboard Cite

show abstract

“…1 Several nonlinear control methods have been proposed to achieve proper performance for the operation of aerospace vehicles. These include model predictive base nonlinear control, 2 trajectory linearization control, 3 adaptive back-stepping, 4 sliding mode control, 5 state-dependent Riccati equation (SDRE) techniques, 6 and adaptive SDRE control. 7 Finite-time convergence usually results in an increased convergence rate, accuracy, and performance over that provided by asymptotic stabilization.…”

Section: Introductionmentioning

confidence: 99%

Finite-horizon servo SDRE for super-maneuverable aircraft and magnetically-suspended CMGs

Geranmehr

Vafaee

Nekoo

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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This work proposes a finite-horizon servo state-dependent Riccati equation (SDRE) to control two classes of aerospace systems. The SDRE is widely used for nonlinear and optimal control of different systems in theory and practice. In this work, an augmented integrator was added to the SDRE (servo SDRE) to increase performance of the controller, especially to decrease steady-state error. The finite-horizon structure developed for servo SDRE features the advantages of both methods. Attitude control of super-maneuverable aircraft was modeled and simulated. It was then compared with a conventional SDRE controller to show the advantages of the proposed combination. A magnetically suspended double-gimbal control moment gyroscope was tested using the finite-horizon servo SDRE because the control moment gyroscope is the primary attitude control actuator for spacecraft. The results showed that the servo structure improved the performance and decreased the error of the SDRE using a simple systematic approach. The finite-horizon option completes the task sooner than common controllers.

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A Lyapunov-based three-axis attitude intelligent control approach for unmanned aerial vehicle

Mazinan

2015

J. Cent. South Univ.

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Attitude controller for reentry vehicles using state-dependent Riccati equation method

Cited by 7 publications

References 7 publications

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Adaptive-gain multivariable super-twisting sliding mode control for reentry RLV with torque perturbation

Finite-horizon servo SDRE for super-maneuverable aircraft and magnetically-suspended CMGs

A Lyapunov-based three-axis attitude intelligent control approach for unmanned aerial vehicle

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