Control Allocation for an Over-Actuated Aircraft Based on Within-Visual-Range Air Combat Agility

Liu, Yan; Gao, Zhenghong; Chong-yang, Shang

doi:10.1109/access.2018.2814958

Cited by 5 publications

(1 citation statement)

References 14 publications

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“…e is an n-dimensional random estimation error, and 𝜣 = [𝜃 1 𝜃 2 ⋯ 𝜃 𝑚 ] 𝑇 is the matrix of unknown parameters to be estimated. Then the fitted regression expression is expressed as follows: (44) where yi is the i th row element of the vector y, xij is the i th row, j th column element of the matrix X, 𝑥 𝑖 = [𝑥 𝑖1 𝑥 𝑖2 ⋯ 𝑥 𝑖𝑚 ] 𝑇 , 𝜣 ̂ is the estimated value of the matrix 𝜣, ei is the estimated error of the i th row, i=1,2,…,n, j=1,2,…,m. The control objective is to estimate the unknown model coefficients θj, j=1,2, … ,m. such that the following leastsquares function (45) obtains the minimum value.…”

Section: )Irls-based Aerodynamic Parameter Estimationmentioning

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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Section: )Irls-based Aerodynamic Parameter Estimationmentioning

confidence: 99%

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

et al. 2021

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Finite-time blended control for air-to-air missile with lateral thrusters and aerodynamic surfaces

Guo

Liu

et al. 2020

Aerospace Science and Technology

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A Modified NSGA-II for Solving Control Allocation Optimization Problem in Lateral Flight Control System for Large Aircraft

2019

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Coordinated aileron and rudder control is crucial to the lateral control stability augmentation of an aircraft. In this paper, a modified non-dominated sorting genetic algorithm II is proposed to not only optimize the control allocation between the aileron and rudder channels on different flying quality levels but also explore the relationships between the optimum solutions and the state variables of the aircraft. In doing so, a digital, nets-based stratification method is used to initialize the search chromosomes more evenly. To improve the search efficiency of the algorithm, crowding-distance-based interpolation and elimination strategies are developed to approach the optimum Pareto frontier as close as possible. Moreover, a dynamic depth search method is proposed to balance between the global and local explorations. Finally, the control allocation relationships between the aileron and rudder channels on different flying quality levels are illustrated. The comparative simulations on a six-degree-of-freedom Boeing 747 model are carried out to verify the feasibility of the proposed algorithm. INDEX TERMS MNSGA-II, control allocation optimization, flight control system.

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Control Allocation for an Over-Actuated Aircraft Based on Within-Visual-Range Air Combat Agility

Cited by 5 publications

References 14 publications

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

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

Finite-time blended control for air-to-air missile with lateral thrusters and aerodynamic surfaces

A Modified NSGA-II for Solving Control Allocation Optimization Problem in Lateral Flight Control System for Large Aircraft

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