Nonlinear hierarchy-structured predictive control design for a generic hypersonic vehicle

Mathematical Problems in Engineering

et al. 2015

Self Cite

We propose a predictive sliding mode control (PSMC) scheme for attitude control of hypersonic vehicle (HV) with system uncertainties and external disturbances based on an improved fuzzy disturbance observer (IFDO). First, for a class of uncertain affine nonlinear systems with system uncertainties and external disturbances, we propose a predictive sliding mode control based on fuzzy disturbance observer (FDO-PSMC), which is used to estimate the composite disturbances containing system uncertainties and external disturbances. Afterward, to enhance the composite disturbances rejection performance, an improved FDO-PSMC (IFDO-PSMC) is proposed by incorporating a hyperbolic tangent function with FDO to compensate for the approximate error of FDO. Finally, considering the actuator dynamics, the proposed IFDO-PSMC is applied to attitude control system design for HV to track the guidance commands with high precision and strong robustness. Simulation results demonstrate the effectiveness and robustness of the proposed attitude control scheme.

Section: Simulation Results Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Predictive Sliding Mode Control for Attitude Tracking of Hypersonic Vehicles Using Fuzzy Disturbance Observer

Cheng

Tang

Mathematical Problems in Engineering

et al. 2015

Self Cite

“…Every parametric uncertainty has two limited values: a positive maximum and a negative minimum. To study the robustness of the control system under different effects of uncertainties, 32 groups of combinations of parametric uncertainties are derived, as shown in [8].…”

Section: Uncertain Parameters and Atmospheric Disturbancementioning

confidence: 99%

“…The term hypersonic vehicle (HV) generally refers to a vehicle flying at Mach 5 or above [1]; such vehicles have become a popular topic in research on the flight control of air vehicles [2][3][4][5][6][7][8][9]. Although they have many advantages, such as a large flight envelope, high maneuverability, and good penetrability, HVs are very sensitive to changes in flight conditions [10,11].…”

Section: Introductionmentioning

confidence: 99%

Sliding mode decoupling control of a generic hypersonic vehicle based on parametric commands

Tang

2014

Sci. China Inf. Sci.

Self Cite

Super twisting sliding mode control for a flexible air-breathing hypersonic vehicle based on disturbance observer SCIENCE CHINA Information Sciences 58, 070207 (2015); Adaptive mode switching of hypersonic morphing aircraft based on type-2 TSK fuzzy sliding mode control SCIENCE CHINA Information Sciences 58, 070205 (2015); Dynamic decoupling tracking control for the polytopic LPV model of hypersonic vehicle SCIENCE CHINA Information Sciences 58, 092203 (2015);Nonlinear hierarchy-structured predictive control design for a generic hypersonic vehicle SCIENCE CHINA Technological Sciences 56, 2025; ${\mathcal{L}}_{1}$ adaptive control of a generic hypersonic vehicle model with a blended pneumatic and thrust vectoring control strategy Abstract A sliding mode decoupling attitude controller based on parametric commands is proposed for a generic hypersonic vehicle (GHV). This vehicle model has fast time variability and strong coupling, is highly nonlinear, and includes uncertain parameters. The design of the controller takes these features into account. First, for the purpose of decoupling, the inner loop of the controller is designed using the dynamic inversion (DI) method. Input/output linearization is achieved using full-state feedback to globally linearize the nonlinear dynamics of selected controlled outputs. Second, to improve the robustness of the attitude control system, the sliding mode control (SMC) method is used to design the outer loop of the controller. Although the DI and SMC methods result in decoupling and robustness, there exists serious inconsistency between the commands of the attitude angles and the commands of the first-order differential of the attitude angles. To solve this problem and achieve a trade-off between dynamic response speed and attitude-tracking precision, we propose a parametric method for calculating the commands of the first-order differential of the attitude angles. Finally, simulation studies are conducted for the trimmed cruise conditions of 33.5 km altitude and Mach 15, and the responses of the vehicle to the step commands of pitch angle, yaw angle, and rolling angle are examined. The simulation studies demonstrate that the proposed controller is robust with respect to the uncertain parameters and atmospheric disturbance and meets the performance requirements of the GHV with acceptable control inputs.controller for an HV [13,14], and it is essential to achieve linearization and decoupling of the dynamic model and to improve the efficiency and robustness of the attitude control system.In the past decades, nonlinear control methods have mainly been used for HVs. The dynamic inversion (DI) method has been widely and successfully used to control nonlinear systems [15][16][17][18] and is considered to be one of the most effective control methods for decoupling. The DI method was proposed by Snell, Enns, and Garrard [16] to resolve problems of nonlinearity and coupling in designing a flight control system for a supermaneuverable aircraft. This approach to nonlinear control design ach...

“…Refs. [8][9][10] design feedback and feedforward controllers for individual axis, and all of them can improve tracking performance effectively. However, because of the servo lag, a good tracking performance for each individual axis does not guarantee further reduction of biaxial synchronous error [11,12].…”

Section: Introductionmentioning

confidence: 99%

Robust adaptive cross-coupling position control of biaxial motion system

Chen

Sci. China Technol. Sci.

Geng

et al. 2015

The stability and synchronous performance are usually hard to be improved simultaneously in the biaxial cross-coupling position motion control system. Based on analyzing the characteristics of the cross-coupling control system, a robust adaptive cross-coupling control strategy is proposed. To restrict influences of destabilizing factors and improve both of stability and synchronous performance, the strategy forces dual axes to track the same reference model using Narendra adaptive control theory. And then, a robust parameters adaptive law is proposed. The stability analysis of the proposed strategy is conducted by applying Lyapunov stability theory. Related simulations and experiments indicate that the proposed strategy can improve synchronous performance and stability simultaneously. biaxial motion, motor control system, position tracking, robust adaptive control, cross-coupling, synchronous error Citation: Chen W, Wang D D, Geng Q, et al. Robust adaptive cross-coupling position control of biaxial motion system. Sci China Tech Sci, 2016, 59: 680688,