The Experts below are selected from a list of 3048 Experts worldwide ranked by ideXlab platform
Qun Zong - One of the best experts on this subject based on the ideXlab platform.
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anti windup robust backstepping control for an underactuated Reusable Launch Vehicle
IEEE Transactions on Systems Man and Cybernetics, 2020Co-Authors: Bailing Tian, Qun Zong, Houde Liu, Bin Liang, Bo YuanAbstract:The attitude control of an underactuated Reusable Launch Vehicle (RLV) in the reentry phase involving nonminimum phase problem and control input constraints is investigated in this article. To address the nonminimum phase problem, an approach combining output redefinition and robust backstepping is proposed, where a synthetic output is constructed using the combination of the original output and the internal states to obtain stable zero dynamics, and then robust backstepping is performed on the new output. Besides, the ideal internal dynamics are obtained by using optimal bounded inversion, which are incorporated into the controller as the reference trajectories for the internal states to improve the output tracking accuracy. To cope with the control input constraints, a simple and useful anti-windup strategy is proposed by using feedback error clipping, which is shown to be very effective in mitigating control input saturation. Numerical simulations are given to validate the effectiveness of the proposed method.
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finite time attitude tracking control design for Reusable Launch Vehicle in reentry phase based on disturbance observer
Advances in Mechanical Engineering, 2017Co-Authors: Fang Wang, Qin Zou, Changchun Hua, Qun ZongAbstract:For the attitude tracking control problem of reentry Reusable Launch Vehicle in reentry phase, a disturbance observer–based sliding mode controller is proposed in this article. At first, attitude m...
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integrated finite time disturbance observer and controller design for Reusable Launch Vehicle in reentry phase
Journal of Aerospace Engineering, 2017Co-Authors: Qi Dong, Qun Zong, Bailing Tian, Fang WangAbstract:AbstractAn integrated finite-time disturbance observer (FDO) and attitude controller is designed for a Reusable Launch Vehicle (RLV) in this paper. In accordance with the multiple-timescale features, RLV attitude dynamics are divided into an outer-loop subsystem and an inner-loop subsystem. Based on the recently developed sliding mode control (SMC), a novel multivariable supertwisting sliding mode controller driven by a FDO is designed to achieve a fast and accurate reentry attitude tracking. This integrated design can generate a continuous control law which has excellent robustness to uncertainty and disturbances with known bounds while achieving an arbitrarily fast convergence. The finite-time stability of the overall system is proved by using the Lyapunov function technique and the multiple-timescale separation principle. In addition, an optimal control allocation for allocating torque commands into aerodynamic surface deflection commands with constraints is also proposed. Finally, the effectiveness an...
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disturbance observer based sliding mode backstepping control for a re entry Vehicle with input constraint and external disturbance
Transactions of the Institute of Measurement and Control, 2016Co-Authors: Fang Wang, Qun Zong, Qi Dong, Bailing TianAbstract:An attitude controller is designed for a Reusable Launch Vehicle (RLV) during the re-entry phase with input constraint, model uncertainty and external disturbance. A control-oriented model with mat...
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attitude control of Reusable Launch Vehicle in reentry phase with input constraint via robust adaptive backstepping control
International Journal of Adaptive Control and Signal Processing, 2015Co-Authors: Fang Wang, Changchun Hua, Qun ZongAbstract:Summary The paper presents an attitude control problem of Reusable Launch Vehicles in reentry phase. The controller is designed based on synthesizing robust adaptive control into backstepping control procedure in the presence of input constraint, model uncertainty, and external disturbance. In view of the coupling between the states of translational motion and the states of attitude motion, the control-oriented model is developed, where the uncertainties do not satisfy linear parameterization assumption. The time derivative of the virtual control input is viewed as a part of uncertain term to facilitate the analytic computations and avoid the ‘explosion of terms’ problem. The robust adaptive backstepping control scheme is first proposed to overcome the uncertainty and external disturbance. The robust adaptive law is employed to estimate the unknown bound of the uncertain term. Furthermore, the attitude control problem subjects to input constraint is studied, and the constrained robust adaptive backstepping control strategy is proposed. Within the Lyapunov theory framework, the stability analysis of the closed-loop system is carried out, and the tracking error converges to a random neighborhood around origin. Six-degree-of-freedom Reusable Launch Vehicle simulation results are presented to show the effectiveness of the proposed control strategy. Copyright © 2015 John Wiley & Sons, Ltd.
Zhifeng Gao - One of the best experts on this subject based on the ideXlab platform.
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active fault tolerant control design for Reusable Launch Vehicle using adaptive sliding mode technique
Journal of The Franklin Institute-engineering and Applied Mathematics, 2012Co-Authors: Moshu Qian, Bin Jiang, Zhifeng Gao, Peng Shi, Jinxing LinAbstract:Abstract In this paper, the problem of active fault tolerant control for a Reusable Launch Vehicle (RLV) with actuator fault using both adaptive and sliding mode techniques is investigated. Firstly, the kinematic equations and dynamic equations of RLV are given, which represent the characteristics of RLV in reentry flight phase. For the dynamic model of RLV in faulty case, a fault detection scheme is proposed by designing a nonlinear fault detection observer. Then, an active fault tolerant tracking strategy for RLV attitude control systems is presented by making use of both adaptive control and sliding mode control techniques, which can guarantee the asymptotic output tracking of the closed-loop attitude control systems in spite of actuator fault. Finally, simulation results are given to demonstrate the effectiveness of the developed fault tolerant control scheme.
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new fault tolerant control scheme design for Reusable Launch Vehicle attitude control systems
IFAC Proceedings Volumes, 2012Co-Authors: Moshu Qian, Bin Jiang, Hugh H T Liu, Zhifeng GaoAbstract:Abstract In this study, a new fault tolerant control approach is proposed for a class of Reusable Launch Vehicle (RLV) attitude control systems. The nonlinear attitude control systems of RLV are given, which represent the dynamic characteristics of RLV in ascent and reentry phases. When actuator loss-of-effectiveness (LOE) faults occur, a new fault tolerant control design is presented using the dynamic surface control technique. Based on Lyapunov stability theory, the ultimate uniform boundedness of the faulty attitude control systems of RLV is analyzed. Finally, simulation results are given to illustrate the efficiency of the proposed approach.
Bailing Tian - One of the best experts on this subject based on the ideXlab platform.
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anti windup robust backstepping control for an underactuated Reusable Launch Vehicle
IEEE Transactions on Systems Man and Cybernetics, 2020Co-Authors: Bailing Tian, Qun Zong, Houde Liu, Bin Liang, Bo YuanAbstract:The attitude control of an underactuated Reusable Launch Vehicle (RLV) in the reentry phase involving nonminimum phase problem and control input constraints is investigated in this article. To address the nonminimum phase problem, an approach combining output redefinition and robust backstepping is proposed, where a synthetic output is constructed using the combination of the original output and the internal states to obtain stable zero dynamics, and then robust backstepping is performed on the new output. Besides, the ideal internal dynamics are obtained by using optimal bounded inversion, which are incorporated into the controller as the reference trajectories for the internal states to improve the output tracking accuracy. To cope with the control input constraints, a simple and useful anti-windup strategy is proposed by using feedback error clipping, which is shown to be very effective in mitigating control input saturation. Numerical simulations are given to validate the effectiveness of the proposed method.
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integrated finite time disturbance observer and controller design for Reusable Launch Vehicle in reentry phase
Journal of Aerospace Engineering, 2017Co-Authors: Qi Dong, Qun Zong, Bailing Tian, Fang WangAbstract:AbstractAn integrated finite-time disturbance observer (FDO) and attitude controller is designed for a Reusable Launch Vehicle (RLV) in this paper. In accordance with the multiple-timescale features, RLV attitude dynamics are divided into an outer-loop subsystem and an inner-loop subsystem. Based on the recently developed sliding mode control (SMC), a novel multivariable supertwisting sliding mode controller driven by a FDO is designed to achieve a fast and accurate reentry attitude tracking. This integrated design can generate a continuous control law which has excellent robustness to uncertainty and disturbances with known bounds while achieving an arbitrarily fast convergence. The finite-time stability of the overall system is proved by using the Lyapunov function technique and the multiple-timescale separation principle. In addition, an optimal control allocation for allocating torque commands into aerodynamic surface deflection commands with constraints is also proposed. Finally, the effectiveness an...
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disturbance observer based sliding mode backstepping control for a re entry Vehicle with input constraint and external disturbance
Transactions of the Institute of Measurement and Control, 2016Co-Authors: Fang Wang, Qun Zong, Qi Dong, Bailing TianAbstract:An attitude controller is designed for a Reusable Launch Vehicle (RLV) during the re-entry phase with input constraint, model uncertainty and external disturbance. A control-oriented model with mat...
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real time trajectory and attitude coordination control for Reusable Launch Vehicle in reentry phase
IEEE Transactions on Industrial Electronics, 2015Co-Authors: Bailing Tian, Wenru Fan, Qun ZongAbstract:The real-time reentry trajectory and attitude coordination control for a Reusable Launch Vehicle (RLV) is a very important and challenging problem. There are many aspects that make the research appealing, such as being able to autonomously replan a new trajectory onboard when the landing site is changed. In order to achieve the goal, an integrated guidance and control architecture is proposed in this paper. First, the offline reentry trajectory is designed based on adaptive Gauss pseudospectral method. Then, the obtained trajectory is used as the initial value guess for real-time reentry trajectory optimization. As a result, the pseudospectral-based optimal feedback reentry guidance is achieved via successive real-time optimal open-loop control which ensures that the guidance system has sufficient robustness for initial reentry perturbations. Furthermore, a multitime scale smooth second-order sliding-mode controller with disturbance observer is proposed to ensure the finite-time reentry attitude tracking despite the model parameter uncertainties and unknown external disturbances. Finally, two representative simulation tests are carried out to demonstrate the effectiveness of the proposed integrated guidance and control architecture for six-degree-of-freedom RLV.
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integrated guidance and control for Reusable Launch Vehicle in reentry phase
Nonlinear Dynamics, 2015Co-Authors: Bailing Tian, Wenru Fan, Qun ZongAbstract:An integrated guidance and control scheme is developed for next generation of Reusable Launch Vehicle (RLV) with the aim to improve the flexibility, safety and autonomy. Firstly, an outer-loop optimal feedback reentry guidance law with online trajectory reshaping capability is designed. Then, a novel reentry attitude control strategy is proposed based on multivariables smooth second-order sliding mode controller and disturbance observer. The proposed control scheme is able to guarantee that the guidance commands generated from the guidance system can be tracked in finite time. Furthermore, a control allocation is integrated in the system in order to transform the control moments to control surface deflection. Finally, some representative simulation tests are conducted to demonstrate the effectiveness of the proposed integrated guidance and control strategy for six-degree-of-freedom RLV.
Ming Zhang - One of the best experts on this subject based on the ideXlab platform.
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liquid spring damper for vertical landing Reusable Launch Vehicle under impact conditions
Mechanical Systems and Signal Processing, 2019Co-Authors: Shuai Yue, Branislav Titurus, Hong Nie, Ming ZhangAbstract:Abstract This research presents the modelling, experimental validation and analysis of the liquid spring damper under impact conditions during the symmetric vertical soft landing of a Reusable Launch Vehicle. A new nonlinear lumped parameter hydraulic model of a liquid spring damper is first established including the variable liquid bulk modulus, entrapped air, flow inertial effects and cavitation phenomena. Then, a simplified nonlinear model of the scaled Reusable Launch Vehicle test prototype is proposed. This dynamic model, which consists of a three degree-of-freedom main body and a single landing leg assembly with one liquid spring damper, is studied under impact conditions. The experimental prototype with the four nominally identical landing legs is experimentally studied. First, the quasi-static spring damper tests are conducted to identify the compressibility and friction parameters. Then, the Reusable Launch Vehicle prototype drop tests are performed to identify the liquid flow parameters, to validate the damper impact response characteristics and to evaluate the full prototype model through its comparison with the experimental data. It is found that a very good match can be established between the predicted and measured quasi-static damper responses. The local damper predictions also indicate good correlation with the impact test results. The landing prototype simulations indicate qualitatively correct predictions with the main observed discrepancies attributed to the simplified and potentially excessively stiff nature of the prototype model.
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dynamic analysis for vertical soft landing of Reusable Launch Vehicle with landing strut flexibility
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 2019Co-Authors: Shuai Yue, Hong Nie, Ming Zhang, Mingyang Huang, He ZhuAbstract:Based on oleo-honeycomb dampers, a 6-DOF vertical soft landing dynamic model for Reusable Launch Vehicle considering landing strut flexibility is constructed. In order to better analyze the lateral...
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optimization and performance analysis of oleo honeycomb damper used in vertical landing Reusable Launch Vehicle
Journal of Aerospace Engineering, 2018Co-Authors: Shuai Yue, Hong Nie, Ming Zhang, Mingyang HuangAbstract:AbstractA dynamic model is proposed and validated to analyze the landing performance of a vertical landing Reusable Launch Vehicle (RLV) with a novel oleo-honeycomb two-stage damper. Based on this ...
Shuai Yue - One of the best experts on this subject based on the ideXlab platform.
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liquid spring damper for vertical landing Reusable Launch Vehicle under impact conditions
Mechanical Systems and Signal Processing, 2019Co-Authors: Shuai Yue, Branislav Titurus, Hong Nie, Ming ZhangAbstract:Abstract This research presents the modelling, experimental validation and analysis of the liquid spring damper under impact conditions during the symmetric vertical soft landing of a Reusable Launch Vehicle. A new nonlinear lumped parameter hydraulic model of a liquid spring damper is first established including the variable liquid bulk modulus, entrapped air, flow inertial effects and cavitation phenomena. Then, a simplified nonlinear model of the scaled Reusable Launch Vehicle test prototype is proposed. This dynamic model, which consists of a three degree-of-freedom main body and a single landing leg assembly with one liquid spring damper, is studied under impact conditions. The experimental prototype with the four nominally identical landing legs is experimentally studied. First, the quasi-static spring damper tests are conducted to identify the compressibility and friction parameters. Then, the Reusable Launch Vehicle prototype drop tests are performed to identify the liquid flow parameters, to validate the damper impact response characteristics and to evaluate the full prototype model through its comparison with the experimental data. It is found that a very good match can be established between the predicted and measured quasi-static damper responses. The local damper predictions also indicate good correlation with the impact test results. The landing prototype simulations indicate qualitatively correct predictions with the main observed discrepancies attributed to the simplified and potentially excessively stiff nature of the prototype model.
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dynamic analysis for vertical soft landing of Reusable Launch Vehicle with landing strut flexibility
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 2019Co-Authors: Shuai Yue, Hong Nie, Ming Zhang, Mingyang Huang, He ZhuAbstract:Based on oleo-honeycomb dampers, a 6-DOF vertical soft landing dynamic model for Reusable Launch Vehicle considering landing strut flexibility is constructed. In order to better analyze the lateral...
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optimization and performance analysis of oleo honeycomb damper used in vertical landing Reusable Launch Vehicle
Journal of Aerospace Engineering, 2018Co-Authors: Shuai Yue, Hong Nie, Ming Zhang, Mingyang HuangAbstract:AbstractA dynamic model is proposed and validated to analyze the landing performance of a vertical landing Reusable Launch Vehicle (RLV) with a novel oleo-honeycomb two-stage damper. Based on this ...
