Nonlinear H∞ robust control applied to F-16 aircraft with mass uncertainty using control surface inverse algorithm

Kung, Chien-Chun

doi:10.1016/j.jfranklin.2008.05.002

Cited by 19 publications

(6 citation statements)

References 25 publications

(27 reference statements)

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“…With the development of space missions, the reliable control scheme is significantly important for the rigid spacecraft. As the part of spacecraft systems, attitude control plays an important role in spacecraft design and has been studied extensively under various scenarios [1][2][3][4][5]. e reliability of attitude control determines that the planned missions can be accomplished successfully or not.…”

Section: Introductionmentioning

confidence: 99%

“…In [7], to alleviate chattering and ensure a smooth control for actuators by SMC, a second-order sliding mode controller based on anti-unwinding control method is proposed for the attitude stabilization of a rigid spacecraft. In [1], nonlinear H∞ robust controller is proposed for F-16 aircraft with mass and moment inertia uncertainties. To solve the associated Hamilton-Jacobi partial differential inequality, a special Lyapunov function with mass and moment inertia uncertainties is considered.…”

Section: Introductionmentioning

confidence: 99%

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Attitude Tracking of Rigid Spacecraft with Actuator Saturation and Fault Based on a Compound Control

Cheng

Yang

Wang

et al. 2020

Mathematical Problems in Engineering

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A compound control based on active disturbance rejection control (ADRC) scheme and slide mode control (SMC) is proposed to investigate the attitude tracking problem for a spacecraft with modeling uncertainties, external disturbances, actuator failures, and actuator saturations simultaneously. A positive term including control input is separated from the system, and then, the active disturbance rejection concept and the extended state observer (ESO) are applied to deal with the general uncertain item caused by uncertainties, external disturbances, actuator failures, and actuator saturations. The sliding mode surface is designed to transform the attitude tracking problem into attitude stabilization problem. In order to deal with the actuator saturations, a saturation degree coefficient and its corresponding adaptive law are introduced. Compared to other existing references, the proposed scheme does not need to know the structure or upper bound information of the inertial matrix uncertainties and external disturbances. Finally, the stability of the closed-loop system is analyzed by using input to state stability theory. Simulation results are given to verify the effectiveness of the proposed scheme. More importantly, the proposed technique can also be applied to the attitude stabilization of other aircraft, such as the attitude of unmanned aerial vehicle and helicopter in maritime rescue.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Attitude Tracking of Rigid Spacecraft with Actuator Saturation and Fault Based on a Compound Control

Cheng

Yang

Wang

et al. 2020

Mathematical Problems in Engineering

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“…They have been employed for lateral control in Bréda et al (2013) and Panahi and Seyedtabaii (2017). An analytic solution to the non-linear H ∞ robust control of a complete six-degree-of-freedom vehicle with mass and moment inertia uncertainties has been presented in Kung (2008). A surviving UAV in a noisy environment using H ∞ has been detailed in López et al (2015).…”

Section: Introductionmentioning

confidence: 99%

Lateral control of an Aerosonde facing tolerance in parameters and operation speed: performance robustness study

Seyedtabaii

Zaker

2018

Transactions of the Institute of Measurement and Control

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The aim is to acquire low variance roll responses (performance robustness) of control of an Aerosonde despite the high level of tolerances in aerodynamic parameters and working speed. In this respect, fractional-order proportional plus integral and derivative (FOPID) is a valuable option; others are H∞ and μ synthesis. FOPID can tolerate system uncertainty by maintaining a wide open-loop flat phase margin band. All three methods are worked out using the linearized system model and deliver (at least initially) high-integer-order controllers. The uncertainty level is not explicitly considered in H∞, but it may be presented in the μ synthesis and FOPID. The uncertainty presentation in the modified fractional-order controller (mFOC) design is through a Φd curve. The Φd curve is fitted to the mean of the upper and lower bands of the phase margins distribution map of the random systems. It is shown that the mFOC design perfectly secures the desired phase margin flatness. The controllers are applied to the roll of an unmanned aircraft vehicle with a 30% tolerance in the aerodynamic parameters, and operation speed and robustness in performance is evaluated. The simulation results indicate that the mFOC design renders more coherent responses than what H∞ and µ synthesis design deliver. This is confirmed through extensive simulations.

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“…Throughout the years, many control strategies for air vehicle f light c ontrol s ystem (FCS) design have been extensively researched. In historical sequence, some of these methods are classical pole placement and simple feedback methods, 1–3 modified linear quadratic regulator and l inear q uadratic G aussian (LQG) controllers, 4–6 modified H∞ control synthesis, 7–9 constrained m odel p redictive c ontrol, 10–12 and variance-constrained controllers. 13–21 Variance-constrained controllers are one of these control techniques.…”

Section: Introductionmentioning

confidence: 99%

Combined outputs variance constrained and input variance constrained design for flight control

Oktay

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, an algorithm combining two different variance constrained control strategies (i.e. output variance constrained: OVC controller and input variance constrained: IVC controller) is developed. Performance of the resulting novel control technique called as combined output and input variance constrained controller is evaluated on helicopters. Their linearized state-space models are used to see feasibility and efficiency of this new strategy (i.e., output and input variance constrained). Closed loop responses of some outputs and inputs of interest and also some outputs out of interest are investigated while using output and input variance constrained for air vehicle flight control system. Then, closed loop performance of output and input variance constrained is compared with respect to the two other classical control techniques (i.e. outputs variance constrained and input variance constrained). Finally, robustness of output and input variance constrained with respect to the modeling uncertainities is examined.

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Nonlinear H∞ robust control applied to F-16 aircraft with mass uncertainty using control surface inverse algorithm

Cited by 19 publications

References 25 publications

Attitude Tracking of Rigid Spacecraft with Actuator Saturation and Fault Based on a Compound Control

Attitude Tracking of Rigid Spacecraft with Actuator Saturation and Fault Based on a Compound Control

Lateral control of an Aerosonde facing tolerance in parameters and operation speed: performance robustness study

Combined outputs variance constrained and input variance constrained design for flight control

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