An ESO-based Attitude Control Method for Non-affine Hypersonic Flight Vehicles

2021 ◽  
Author(s):  
Yao Lu ◽  
Xiaodong Liu ◽  
Zhiqiang Jia
Keyword(s):  
Attitude Control ◽  
Control Method ◽  
Hypersonic Flight ◽  
Flight Vehicles

scholarly journals Guardian Map Approach to Feasible Range of Static Stability Margin of Hypersonic Flight Vehicles with Input Saturation

2020 ◽  
Vol 2020 ◽  
pp. 1-11
Author(s):  
Hao Lei ◽  
Boyi Chen ◽  
Yanbin Liu ◽  
Yuping Lu
Keyword(s):  
Flight Control ◽  
Attitude Control ◽  
Integrated Control ◽  
Input Saturation ◽  
Stability Margin ◽  
Static Stability ◽  
Linear Matrix ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Feasible Range

Static stability margin is a critical parameter in flight control design. The feasible range of it must cover the uncertainty through the flight. To reasonably identify the feasible range of static stability margin in advance, an approach based on guardian maps is proposed for flight control of hypersonic flight vehicles with input saturation. First, the model of hypersonic flight vehicle (HFV) is established as a parametric plant. Then, flying quality requirements for the closed-loop system are formulated as inequality constraints using guardian maps. Moreover, by using linear matrix inequality, the saturation of elevators is taken into account in the integrated control of attitude control. The prescribed minimum of static stability margin that ensures the flying quality of hypersonic flight vehicles with input saturation is obtained. Furthermore, from the prospective of integrated control, it is shown that the feasible range of static stability margin can be enlarged by changing aerodynamic characteristics. The effectiveness of the proposed approach is validated by numerical simulation.

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

2017 ◽  
Vol 232 (5) ◽  
pp. 1002-1011
Author(s):  
Wubin Zhen ◽  
Yuhui Wang ◽  
Qingxian Wu ◽  
Peng Shao
Keyword(s):  
Attitude Control ◽  
Sampling Method ◽  
Hypersonic Vehicle ◽  
Flight Vehicle ◽  
Statistical Sampling ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Attitude Tracking ◽  
Simulation Results ◽  
Negative Impacts

At hypersonic speed, strong nonlinear couplings will bring enormous challenges to the attitude control of a hypersonic flight vehicle. To reduce the negative impacts of the couplings, a hierarchical coordinated controller is proposed for a generic hypersonic vehicle in this paper. By using a statistical sampling method, a series of coupling analyses between any two different attitude variables groups are studied firstly, and the matrices that describe the coupling degrees are provided. Based on the coupling degree matrices, two coordinated controllers are designed for the attitude angles and angular rates, respectively. The simulation results indicate that the proposed controller can effectively coordinate the coupling impacts, and achieve smooth attitude tracking.

A novel adaptive dynamic surface control scheme of hypersonic flight vehicles with thrust and actuator constraints

2017 ◽  
Vol 40 (4) ◽  
pp. 1362-1374 ◽  
Author(s):  
Shen Zhang ◽  
Qing Wang ◽  
Chaoyang Dong
Keyword(s):  
Control Method ◽  
Dynamic Surface Control ◽  
Tracking Errors ◽  
Dynamic Surface ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Surface Control ◽  
Adaptive Law ◽  
Control Scheme ◽  
Actuator Constraints

In this paper, the nonlinear adaptive velocity and altitude tracking controller is developed for the longitudinal dynamics of generic air-breathing hypersonic flight vehicles. The proposed control scheme is designed using dynamic surface control method. The velocity and altitude subsystems are transformed into the linearly parameterized form for the convenience of adaptive law design. Both of the thrust and actuator constraints are explicitly considered. For thrust constraint, two cases are analyzed when the fuel-to-air ratio reaches its max and min values. A novel adaptive law is proposed to avoid over or less estimation in thrust saturation occasion. For actuator constraint, a magnitude and rate limiting filter is incorporated. The filter guarantees that the control signal is applicable for the actuator. It is shown that with the application of the proposed control scheme, all signals of the closed-loop system are uniformly ultimately bounded and the velocity and altitude tracking errors converge to a residual set which is arbitrarily small. Simulation results are demonstrated to show the effectiveness and superiority of the proposed control scheme.

scholarly journals Design and validation of an MPC controller for CMG-based testbed

2021 ◽  
Author(s):  
Matteo Facchino ◽  
Atsushi Totsuka ◽  
Elisa Capello ◽  
Satoshi Satoh ◽  
Giorgio Guglieri ◽  
...  
Keyword(s):  
Predictive Control ◽  
Attitude Control ◽  
High Speed ◽  
Control Method ◽  
Input Constraints ◽  
Virtual Reference ◽  
Control Moment ◽  
Pyramidal Configuration ◽  
Actuation Systems ◽  
Constraints Satisfaction

AbstractIn the last years, Control Moment Gyros (CMGs) are widely used for high-speed attitude control, since they are able to generate larger torque compared to “classical” actuation systems, such as Reaction Wheels . This paper describes the attitude control problem of a spacecraft, using a Model Predictive Control method. The features of the considered linear MPC are: (i) a virtual reference, to guarantee input constraints satisfaction, and (ii) an integrator state as a servo compensator, to reduce the steady-state error. Moreover, the real-time implementability is investigated using an experimental testbed with four CMGs in pyramidal configuration, where the capability of attitude control and the optimization solver for embedded systems are focused on. The effectiveness and the performance of the control system are shown in both simulations and experiments.

scholarly journals Deformation Reconstruction and High-Precision Attitude Control of a Launch Vehicle Based on Strain Measurements

2021 ◽  
Vol 2021 ◽  
pp. 1-20
Author(s):  
Liang Zhuang ◽  
Zhang Yulin
Keyword(s):  
High Precision ◽  
Attitude Control ◽  
Control Method ◽  
Launch Vehicles ◽  
Bending Vibration ◽  
Inverse Control ◽  
Deformation Parameters ◽  
Control Framework ◽  
Fbg Sensors ◽  
Dynamic Inverse

The development of launch vehicles has led to higher slenderness ratios and higher structural efficiencies, and the traditional control methods have difficulty in meeting high-quality control requirements. In this paper, an incremental dynamic inversion control method based on deformation reconstruction is proposed to achieve high-precision attitude control of slender launch vehicles. First, the deformation parameters of a flexible rocket are obtained via fiber Bragg grating (FBG) sensors. The deformation and attitude information is introduced into the incremental dynamic inverse control loop, and an attitude control framework that can alleviate bending vibration and deformation is established. The simulation results showed that the proposed method could accurately reconstruct the shapes of flexible launch vehicles with severe vibration and deformation, which could improve the accuracy and stability of attitude control.

scholarly journals Disturbance observer-based control for nonlinear systems subject to mismatched disturbances with application to hypersonic flight vehicles

2017 ◽  
Vol 14 (2) ◽  
pp. 172988141769914 ◽  
Author(s):  
Yunling Li ◽  
Ming Zeng ◽  
Hao An ◽  
Changhong Wang
Keyword(s):  
Nonlinear Systems ◽  
Disturbance Observer ◽  
State Of The Art ◽  
Output Channel ◽  
Tracking Problem ◽  
Gain Matrix ◽  
Hypersonic Flight ◽  
Flight Vehicles ◽  
Nominal Performance ◽  
Mismatched Disturbances

For a class of multi-input multi-output nonlinear systems, a disturbance observer-based control is proposed to solve the tracking problem in the presence of mismatched disturbances. By designing a novel compensation gain matrix, the disturbances can be removed from the output channel completely as well as retaining the nominal performance. Compared with the state of the art, the gain matrix reduces to be constant; therefore, the complexity of the controller is simplified greatly. This method is applied to the control of hypersonic flight vehicles to demonstrate its effectiveness.

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