Dynamic analysis of a variable-span, variable-sweep morphing UAV

Prabhakar, Nirmit; Prazenica, Richard J.; Gudmundsson, Snorri

doi:10.1109/aero.2015.7119089

Cited by 19 publications

(10 citation statements)

References 4 publications

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“…In (13), the varying parameter θ is omitted for brevity because θ must always be included in the varying parameter set. In the proposed method, x 3 is excluded from the varying parameter set by JL.…”

Section: A Proposed Improvements Of Fsmentioning

confidence: 99%

“…The main reason is that morphing will lead to nonlinear and non-stationary aerodynamics with uncertainty and parameter-variation [13]. The main reason is that morphing will lead to nonlinear and non-stationary aerodynamics with uncertainty and parameter-variation [13].…”

Section: Introductionmentioning

confidence: 99%

“…However, there are still very few effective MUAVs used in practice. The main reason is that morphing will lead to nonlinear and non‐stationary aerodynamics with uncertainty and parameter‐variation . Such obstacles are a great challenge for modeling and control design.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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: A Proposed Improvements Of Fsmentioning

confidence: 99%

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, Datcom is employed to calculate these derivatives for the aircraft when symmetric planform changes are implemented for that we focus on the longitudinal altitude controller design. To reduce the difficulties in calculating aerodynamic parameters at the basis of guarantee accuracy, the following assumptions are made which are commonly used [1,15]:…”

Section: Aerodynamic Parametersmentioning

confidence: 99%

Nonlinear robust adaptive NN control for variable-sweep aircraft

Ma¹,

Feng²,

Hu³

et al. 2018

J. vibroeng.

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In this paper, we address the problem of altitude and velocity controllers design for variable-sweep aircraft with model uncertainties. The object is to maintain altitude and velocity during the wing transition process where mass distribution and aerodynamic parameters change significantly. Based on the functional decomposition, the longitudinal dynamics of the aircraft can be divided into altitude subsystem in non-affine pure feedback form and velocity subsystem. And then nonlinear robust adaptive NN velocity controller and altitude controller are designed with backstepping method to relax the prior requirements of aerodynamic parameters accuracy in linear LPV controller design. The method of filtered signal is used to circumvent the algebraic loop problem caused by the dynamics of non-affine pure feedback form. Dynamic surface control (DSC) and minimal learning parameters (MLP) techniques are employed to solve the problems of 'explosion of complexity' in the back-stepping method and the online updated parameters being too much. The robust terms have been introduced to eliminate the influences of approximation errors. According to the Lyapunov-LaSalle invariant set theorem, the semi-global boundedness and convergence of all the signals of the closed-loop system are proved. Simulation results are presented to illustrate the control algorithm with good performance.

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“…Both these researchers outlined suitable mission paths for optimal performance according to their respective morphing schemes. Prabhakar et al [19] discussed the longitudinal dynamics of morphing aircraft with variable wingspan and sweep by trimming the aircraft for specific speeds and altitudes. Computation of aerodynamic coefficients and stability analysis were performed using Vortex Lattice Method (VLM) code in researches referenced as [17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Stability Characteristics of Wing Span and Sweep Morphing for Small Unmanned Air Vehicle: A Mathematical Analysis

Umer

Maqsood

Riaz

et al. 2020

Mathematical Problems in Engineering

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Morphing aircraft are the flight vehicles that can reconfigure their shape during the flight in order to achieve superior flight performance. However, this promising technology poses cross-disciplinary challenges that encourage widespread design possibilities. This research aims to investigate the flight dynamic characteristics of various morphed wing configurations that can be incorporated in small-scale UAVs. The objective of this study was to analyze the effects of in-flight wing sweep and wingspan morphing on aerodynamic and flight stability characteristics. Longitudinal, lateral, and directional characteristics were evaluated using linearized equations of motion. An open-source code based on Vortex Lattice Method (VLM) assuming quasi-steady flow was used for this purpose. Trim points were identified for a range of angles of attack in prestall regime. The aerodynamic coefficients and flight stability derivatives were compared for the aforementioned morphing schemes with a fixed-wing counterpart. The results indicated that wingspan morphing is better than wing sweep morphing to harness better aerodynamic advantages with favorable flight stability characteristics. However, extension in wingspan beyond certain limits jeopardizes the advantages. Dynamically, wingspan and sweep morphing schemes behave in an exactly opposite way for longitudinal modes, whereas lateral-directional dynamics act in the same fashion for both morphing schemes. The current study provided a baseline to explore the advanced flight dynamic aspects of employed wing morphing schemes.

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Dynamic analysis of a variable-span, variable-sweep morphing UAV

Cited by 19 publications

References 4 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

Nonlinear robust adaptive NN control for variable-sweep aircraft

Stability Characteristics of Wing Span and Sweep Morphing for Small Unmanned Air Vehicle: A Mathematical Analysis

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