Kalman-filter-based robust control for hypersonic flight vehicle with measurement noises

Liang, Shan; Xu, Bin; Ren, Jinrui

doi:10.1016/j.ast.2021.106566

Cited by 19 publications

(12 citation statements)

References 46 publications

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“…where τ δ > 0 and ω δ > 0; the specific definitions of H δ ð•Þ and H Ψ ð•Þ are given by equations ( 10) and (11).…”

Section: Controller Designmentioning

confidence: 99%

“…At present, the commonly used idea is to design controllers for the inputoutput subsystem based on output redefinition method [3,4]. An alternative method which is available for dealing with the controller design problem of such a strong nonlinear system as HFV is backstepping approach [5][6][7][8][9][10][11]. The backstepping method is applied firstly to the attitude control of HFV in Ref.…”

Section: Introductionmentioning

confidence: 99%

“…The problem of "differential explosion" occurs easily in the design of the backstepping controller due to the high order of the altitude subsystem of HFV. To solve the problem, the command filter [6], dynamic surface control [8,9], tracking differentiator [10,11], and other technologies are widely used in the backstepping control method. To deal with uncertainties as well as external disturbance of HFV, disturbance observers [12,13] and intelligent approximations [14][15][16] are widely used in controller design.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Backstepping Control Based on Constrained Command Filter for Hypersonic Flight Vehicles with AOA and Actuator Constraints

Wei

Guo

et al. 2021

International Journal of Aerospace Engineering

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An antisaturation backstepping control scheme based on constrained command filter for hypersonic flight vehicle (HFV) is proposed with the consideration of angle of attack (AOA) constraint and actuator constraints of amplitude and rate. Firstly, the HFV system model is divided into velocity subsystem and height subsystem. Secondly, to handle AOA constraint, a constrained command filter is constructed to limit the amplitude of the AOA command and retain its differentiability. And the constraint range is set in advance via a prescribed performance method to guarantee that the tracking error of the AOA meets the constraint conditions and transient and steady performance. Thirdly, the proposed constrained command filter is combined with the auxiliary system for actuator constraints, which ensures that the control input meets the limited requirements of amplitude and rate, and the system is stable. In addition, the tracking errors of the system are proved to be ultimately uniformly bounded based on the Lyapunov stability theory. Finally, the effectiveness of the proposed method is verified by simulation.

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“…where τ δ > 0 and ω δ > 0; the specific definitions of H δ ð•Þ and H Ψ ð•Þ are given by equations ( 10) and (11).…”

Section: Controller Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Backstepping Control Based on Constrained Command Filter for Hypersonic Flight Vehicles with AOA and Actuator Constraints

Wei

Guo

et al. 2021

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…The system states of HFV are usually difficult to be accurately measured due to sensor noises and complex flight environment, which makes the controller design extremely difficult. In [2], the tracking control problem of hypersonic flight vehicle (HFV) with measurement noises and system uncertainties were investigated. To deal with such a problem, a linear quadratic Gaussian (LQG) optimal control algorithm and a robust back-stepping control strategy are proposed using Kalman filter.…”

Section: Introductionmentioning

confidence: 99%

Sensor and Process Noises Reduction using a Luenberger State Estimator with a Stability Augmentation System for a Hypersonic Transport Aircraft

Zaludin

2022

ARME

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This paper firstly, presents an autopilot strategy for a Hypersonic Transport Aircraft (HST) using a Stability Augmentation System (SAS) with a Luenberger estimator. The SAS is designed using Linear Quadratic Regulator (LQR) theory which, for HST, benefits the guaranteed robust dynamic stability provided three theoretical requirements are met. The Luenberger estimator is incorporated into the autopilot design to estimate the state variables of the aircraft for the SAS. In the dynamic response simulation, sensor and process noises are inserted into the mathematical model. However, to date, knowledge of the sensor and process noises at the speeds and heights where the aircraft will be flying is limited. The simulation shows that the Luenberger estimator significantly filters the noise. This is an advantage for the HST as prior knowledge of the noises is not necessary when designing the Luenberger estimator.

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“…And the aerodynamic parameters will change with the changes in flight speed, altitude and atmospheric density. Fighters usually adopt a statically unstable aerodynamic layout to achieve better maneuverability, such as F-16 fighters [3], which increases the fighter's sensitivity to parameter uncertainties. In order to enable the fighter to fly safely and reliably with good maneuverability under predictable parameter changes, eliminating the influence of uncertain parameters on system performance is an important research topic in the control of such uncertain nonlinear systems [4][5][6][7].…”

Section: Introductionmentioning

confidence: 99%

Hybird Nonlinear Control for Fighter With Center of Gravity Perturbation and Aerodynamic Parameter Uncertainty

et al. 2021

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In this paper, a hybrid nonlinear control scheme combines nonlinear dynamic inversion (NDI) and adaptive sliding mode (ASM) control is proposed for high angle of attack fighter system with center of gravity perturbation and aerodynamic parameter uncertainty. By introducing the affine nonlinear model of inner loop angular velocity with center of gravity perturbation, an adaptive sliding mode control scheme based on the online estimation of radial basis function (RBF) neural network is designed, which can reduce the dynamic inversion error of NDI control and rapidly compensate the multi-coupled channel oscillation. The aerodynamic force and moment coefficients are estimated via the iterative weighted least squares (IRLS) method. The outer loop integral sliding mode (ISM) NDI controller is designed, which can be robust to disturbances and mismatched uncertainties through adjusting adaptive gain, and the rudder yaw chattering caused by the uncertainty of aerodynamic parameters is reduced simultaneously. The Lyapunov stability theory and Barbarat lemma prove the stability of the designed control scheme, and the effectiveness of the hybrid nonlinear control scheme is verified based on F-16 model.

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Kalman-filter-based robust control for hypersonic flight vehicle with measurement noises

Cited by 19 publications

References 46 publications

Backstepping Control Based on Constrained Command Filter for Hypersonic Flight Vehicles with AOA and Actuator Constraints

Backstepping Control Based on Constrained Command Filter for Hypersonic Flight Vehicles with AOA and Actuator Constraints

Sensor and Process Noises Reduction using a Luenberger State Estimator with a Stability Augmentation System for a Hypersonic Transport Aircraft

Hybird Nonlinear Control for Fighter With Center of Gravity Perturbation and Aerodynamic Parameter Uncertainty

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