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

Abstract

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...

Prescribed Performance Tracking Control for Hypersonic Flight Vehicles with Model Uncertainties

“…Obviously, it is impossible to design the controller directly from inequality (10). In this paper, we introduce an error transformation function as follows:…”

“…[9] investigates a novel model-free controller for the HFV longitudinal motion model. Since the HFV model has fast time variability, strong coupling, and highly nonlinear and uncertain parameters, a sliding-mode decoupling attitude controller based on parametric commands is proposed which takes these features into account [10]. In order to facilitate the design of the controller, the input and output linearized high-order model of HFV is transformed into a multivariable second-order system model by introducing auxiliary error variables.…”

Coordinated attitude control of hypersonic flight vehicles based on the coupling analysis

“…The following mathematical model is considered to describe the attitude dynamics of a generic HFV [27][28]…”

“…Theorem 1. Consider the attitude dynamics given by equations (1) and 2, and the control law defined by equations (28) and (34), the output i and ! i can asymptotically track the desired signal ci and !…”

Decoupling Attitude Control of a Hypersonic Glide Vehicle Based on a Nonlinear Extended State Observer

“…To sum up, the couplings induced by the above factors between the three channels of the aircraft are very serious, and the controlled plant-the aircraft model, is a multivariable, strongly coupled time-varying system. Especially, the coupling between the lateral channels will result in a large side angle of the aircraft, which is a serious threat to flight safety [3,4]. In order to guarantee the accurate tracking of the guidance command, the flight control system must be able to overcome the adverse effects of the channel coupling.…”