Reconfigurable Nonlinear Dynamic Inversion for Attitude Control of a Structurally Damaged Aircraft

He, Qinming; Tan, Yonghong; Liu, Xiaoxiong; Jia, Qianlei; Liu, Jinglong

doi:10.1109/access.2020.3035436

Cited by 11 publications

(5 citation statements)

References 31 publications

(27 reference statements)

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“…− ∆u(k) ≥ −∆u max (25) ∆u(k) ≥ ∆u min (26) Second, limit the input amplitude at time k within the specified range. The inequality constraints are as follows.…”

Section: Mimo Mfac Methods With Hard Constraintsmentioning

confidence: 99%

See 1 more Smart Citation

A Model Free Adaptive Scheme for Integrated Control of Civil Aircraft Trajectory and Attitude

Jiang

Liu

2021

Symmetry

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The adaptive trajectory and attitude control is essential for the four-dimensional (4D) trajectory operation of civil aircraft in symmetric thrust flight. In this work, an integrated trajectory and attitude control scheme is proposed based on the =multi-input multi-output (MIMO) model free adaptive control (MFAC) method. First, the full-form dynamic linearization technique is adopted to build the equivalent data model of aircraft. Also, the MIMO MFAC scheme with saturation constraint is designed to achieve an accurate tracking control for a given 4D trajectory and attitude. Besides, the performance limitations of aircraft are taken into consideration, and the MIMO MFAC scheme with hard constraints is designed. In addition, to improve the simulation efficiency, a control scheme with mixed constraints, i.e., saturation and hard constraints, is further proposed. It can be seen from the simulation results that the proposed method can perform an integrated control of the aircraft 4D trajectory and attitude without precise modeling, and the control performance is better than that of the model-based control method in terms of flight altitude and yaw angle control. The integrated data-driven control scheme proposed in this paper provides a theoretical solution for the precise operation of aircraft under 4D trajectory.

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“…− ∆u(k) ≥ −∆u max (25) ∆u(k) ≥ ∆u min (26) Second, limit the input amplitude at time k within the specified range. The inequality constraints are as follows.…”

Section: Mimo Mfac Methods With Hard Constraintsmentioning

confidence: 99%

“…Also, the authors in [23] established a model free adaptive attitude control method for launching the vehicle. In addition, the attitude control of aircraft under high angle of attack when the stall occurs and attitude control of a structurally damaged aircraft were respectively studied in [24,25].…”

Section: Introductionmentioning

confidence: 99%

A Model Free Adaptive Scheme for Integrated Control of Civil Aircraft Trajectory and Attitude

Jiang

Liu

2021

Symmetry

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show abstract

“…The characteristics of aircraft include complex flight environment, strong nonlinearity of the model, and so on. Nonlinear control of aircraft [1][2][3] has always been a hot and challenging problem in the field of control. The tracking control of aircraft track angle [4][5] is a particularly important part of the aircraft control system, which has been widely used in aircraft system design.…”

Section: Introductionmentioning

confidence: 99%

Command Filter AILC for Finite Time Accurate Tracking of Aircraft Track Angle System Based on Fuzzy Logic

Zhang,

Tian,

Gao

et al. 2023

Advances in Mathematical Physics

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In this paper, the longitudinal model of an uncertain aircraft is taken as the research object, and the aircraft path inclination is controlled by controlling the input rudder deflection angle. An adaptive iterative learning control (AILC) scheme is proposed to solve the accurate tracking control problem of the flight path inclination on a finite time interval. The aircraft track angle system is abstractly modeled to obtain a triangular model in the form of strict feedback. For the abstracted strict feedback model, the fuzzy logic is used to approximate the uncertain part of the model. A command filter and an error compensation mechanism are introduced to prevent the computational bloat problem caused by excessive system order, and a convergent series sequence is used to deal with the truncation error caused by the approximation of the fuzzy logic. Based on the Lyapunov stability theorem, all signals of the closed-loop system are bounded on the finite time interval 0 , T , and the output of the system can track the desired trajectory accurately. Finally, the feasibility and effectiveness of the method are verified by MATLAB simulation results.

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“…Ref. [28] proposed a reconfigurable nonlinear dynamic inversion (RNDI) controller, which combines a nonlinear disturbance observer (NDO) and improved NDI control for attitude control of structurally damaged aircraft. Adaptive NDI control is also used in variable structure aircraft.…”

Section: Introductionmentioning

confidence: 99%

Improved Adaptive NDI Flight Control Law Design Based on Real-Time Aerodynamic Identification in Frequency Domain

Zhou

Jin

2023

Applied Sciences

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The traditional aircraft controller design is usually based on the off-line aerodynamic model. Due to the deviation of the off-line aerodynamic model, the flight quality is difficult to meet the requirements when the aircraft is flying in the real atmosphere. To solve this problem, this paper proposes a frequency domain identification-based improved adaptive nonlinear dynamic inversion (NDI) control method (FDI-ANDI). In this paper, an online recursive aerodynamic parameter identification method in the frequency domain is first designed, and then an adaptive dynamic inversion control method based on the online aerodynamic parameter identification results is established. Finally, aiming at the problem of the slow response speed of the NDI controller, an improved adaptive dynamic inversion control law is designed by using the method of series lead correction. Compared with the traditional control method, the adaptive dynamic inversion method based on online aerodynamic identification has stronger robustness and a faster response speed in the face of model uncertainty. The final simulation analysis shows that the method has a better control effect than the traditional control method.

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Reconfigurable Nonlinear Dynamic Inversion for Attitude Control of a Structurally Damaged Aircraft

Cited by 11 publications

References 31 publications

A Model Free Adaptive Scheme for Integrated Control of Civil Aircraft Trajectory and Attitude

A Model Free Adaptive Scheme for Integrated Control of Civil Aircraft Trajectory and Attitude

Command Filter AILC for Finite Time Accurate Tracking of Aircraft Track Angle System Based on Fuzzy Logic

Improved Adaptive NDI Flight Control Law Design Based on Real-Time Aerodynamic Identification in Frequency Domain

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