Dynamic Modeling and Active Morphing Trajectory-Attitude Separation Control Approach for Gull-Wing Aircraft

Guo, Tianhao; Hou, Zhanqiang; Zhu, Boqing

doi:10.1109/access.2017.2743059

Cited by 20 publications

(5 citation statements)

References 28 publications

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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%

“…Currently, there are few studies that consider both trajectory tracking and attitude control in the 4D trajectory operation, and the existing research is mainly divided into separate control and integrated control for this problem. In terms of separate control, the literature [26] achieves separate control of trajectory and attitude following the feedforward H ∞ and dynamic inversion control methods. In the research of [5], indirect and direct NLI (Non-Linear Inversion) control methods are used respectively to realize aircraft trajectory control.…”

Section: Introductionmentioning

confidence: 99%

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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%

Section: Introductionmentioning

confidence: 99%

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

Jiang

Liu

2021

Symmetry

View full text Add to dashboard Cite

show abstract

“…In [16], an accurate nonlinear dynamic model of morphing gullwing aircraft was built with additional morphing terms. A state feedback with a feedforward H∞ control approach for an LPV system was applied to the attitude control and a dynamic inversion control approach was designed for the trajectory tracking control.…”

Section: Introductionmentioning

confidence: 99%

Longitudinal Tracking Control for a Morphing Waverider Using Adaptive Super Twisting Control

et al. 2021

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The morphing aircraft is a promising solution to achieve an optimal flight performance according to various mission scenarios. To apply the morphing technology in hypersonic vehicles, a variable-sweep-wing morphing waverider was proposed in previous studies, and its aerodynamic performance and dynamic model were presented. In this paper, this morphing waverider is assumed to perform a long-range unpowered glide mission over a wide speed range from hypersonic to subsonic speed. First, the accurate longitudinal dynamic model for the morphing waverider is presented, with all the additional forces and moments that stem from morphing. And a control-oriented longitudinal dynamic model is proposed and it separates the additional morphing forces and moments from derivatives of state variables. Then, an adaptive super twisting sliding mode controller is applied for this morphing waverider to track the optimized trajectory during the entire morphing process. Finally, the overall performance of this controller is examined by nominal condition simulations and Monte Carlo runs. Under the nominal condition simulations, the adaptive super twisting algorithm based sliding mode controller reduces mean tracking error of the pitch angle by 25% compared with the traditional sliding mode controller. In the 500 Monte Carlo runs, the ASTA controller reduces maximum tracking error of the pitch angle by 47% compared with the SMC controller.INDEX TERMS Variable-sweep-wing, morphing waverider, sliding mode control, adaptive super twisting algorithm

show abstract

“…In [20], an accurate nonlinear dynamic model of morphing gullwing aircraft was built with additional morphing terms. A state feedback with a feedforward H∞ control approach for an LPV system was applied to the attitude control and a dynamic inversion control approach was designed for the trajectory tracking control.…”

Section: Introductionmentioning

confidence: 99%

Modeling and Nonlinear Model Predictive Control of a Variable-Sweep-Wing Morphing Waverider

et al. 2021

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Dynamic Modeling and Active Morphing Trajectory-Attitude Separation Control Approach for Gull-Wing Aircraft

Cited by 20 publications

References 28 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

Longitudinal Tracking Control for a Morphing Waverider Using Adaptive Super Twisting Control

Modeling and Nonlinear Model Predictive Control of a Variable-Sweep-Wing Morphing Waverider

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