Flight dynamic modeling and control for a telescopic wing morphing aircraft via asymmetric wing morphing

Yue, Ting; Zhang, Xiangyang; Wang, Lixin; Ai, Junqiang

doi:10.1016/j.ast.2017.08.013

Cited by 56 publications

(24 citation statements)

References 16 publications

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“…Substituting (19)- (22) with the input affine assumption as (24) and (25) into (18), the nonlinear model of the longitudinal system for MUAV can be written as: Substitute the aerodynamic data and propulsion data into equation of motion.…”

Section: B Application On Muavmentioning

confidence: 99%

“…Therefore, robust GS control based on an LPV system would be an effective method for flight control of MUAVs, especially for the morphing process. Most research on flight control of MUAVs in the transient process focuses on the robust GS control method . Most existing works adopt a control framework that extends norm‐based dynamic feedback robust control to the LPV system, such as output feedback or state feedback H ∞ /H 2 control.…”

Section: Introductionmentioning

confidence: 99%

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Model and robust gain‐scheduled PID control of a bio‐inspired morphing UAV based on LPV method

Shao

et al. 2019

Asian Journal of Control

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In this paper, a linear parameter-varying (LPV)-based model and robust gainscheduled structural proportion integral and derivative (PID) control design solution are proposed and applied on a bio-inspired morphing wing unmanned aerial vehicle (UAV) for the morphing process. In the LPV model method, the authors propose an improved modeling method for LPV systems. The method combines partial linearization and function substitution. Using the proposed method, we can choose the varying parameters simply, thus creating a model that is more flexible and applicable. Then, a robust gain-scheduled structural PID control design method is given by introducing a structural matrix to design a structural PID controller, which is more consistent with the structure of the PID controller used in practice and has a simpler structure than representative ones in the existing literature. The simulation results show that the developed LPV morphing UAV model is able to catch the response of the original nonlinear model with a smaller error than the existing Jacobian linearization method and the designed controller can maintain stable flights in practice with satisfactory robustness and performance.

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Section: B Application On Muavmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Model and robust gain‐scheduled PID control of a bio‐inspired morphing UAV based on LPV method

Shao

et al. 2019

Asian Journal of Control

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“…In [16], Xu et al developed deep neural networks and reinforcement learning techniques as a control strategy of the morphing aircraft. A six-degrees of freedom nonlinear time-varying model and sliding mode flight controller were proposed in [17] to enhance the lateral maneuverability for a tailless telescopic wing morphing aircraft by using additional asymmetric wing telescoping. Wang et al [18] investigated the control problem of a morphing aircraft with variable sweep wings based on switched nonlinear systems and adaptive dynamic programming.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2021

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“…There are a few studies that examine more unconventional methods for generating yawing moments on tailless aircraft. Yue et al [16] explored the use of asymmetrically deployed telescopic wings. However, the influence on rolling moment was an order of magnitude greater than the yawing moment, limiting the usefulness of the concept.…”

Section: Introductionmentioning

confidence: 99%

A Novel Control Allocation Method for Yaw Control of Tailless Aircraft

et al. 2020

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Tailless aircraft without vertical stabilisers typically use drag effectors in the form of spoilers or split flaps to generate control moments in yaw. This paper introduces a novel control allocation method by which full three-axis control authority can be achieved by the use of conventional lift effectors only, which reduces system complexity and control deflection required to achieve a given yawing moment. The proposed method is based on synthesis of control allocation modes that generate asymmetric profile and lift induced drag whilst maintaining the lift, pitching moment and rolling moment at the trim state. The method uses low order models for aerodynamic behaviour characterisation based on thin aerofoil theory, lifting surface methodology and ESDU datasheets and is applied to trapezoidal wings of varying sweep and taper. Control allocation modes are derived using the zero-sets of surrogate models for the characterised aerodynamic behaviours. Results are presented in the form of control allocations for a range of trimmed sideslip angles up to 10 degrees optimised for either maximum aerodynamic efficiency (minimum drag for a specific yawing moment) or minimum aggregate control deflection (as a surrogate observability metric). Outcomes for the two optimisation objectives are correlated in that minimum deflection solutions are always consistent with efficient ones. A configuration with conventional drag effector is used as a reference baseline. It is shown that, through appropriate allocation of lift based control effectors, a given yawing moment can be produced with up to a factor of eight less aggregate control deflection and up to 30% less overall drag compared to use of a conventional drag effector.

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Flight dynamic modeling and control for a telescopic wing morphing aircraft via asymmetric wing morphing

Cited by 56 publications

References 16 publications

Model and robust gain‐scheduled PID control of a bio‐inspired morphing UAV based on LPV method

Model and robust gain‐scheduled PID control of a bio‐inspired morphing UAV based on LPV method

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

A Novel Control Allocation Method for Yaw Control of Tailless Aircraft

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