Multi-Axis Inputs for Identification of a Reconfigurable Fixed-Wing UAV

Lichota, Piotr

doi:10.3390/aerospace7080113

Cited by 16 publications

(6 citation statements)

References 34 publications

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“…One of the main applications of aircraft simulation models is model-based control design as in [9,10]. In order to guarantee a close match to the real aircraft system, identification can be used to improve the accuracy of the models [11,12].…”

Section: Underlying Aircraft Simulation Modelmentioning

confidence: 99%

Required Moment Sets: Enhanced Controllability Analysis for Nonlinear Aircraft Models

et al. 2021

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Attainable moment sets (AMS) are a powerful method to assess aircraft controllability. However, as attainable moment sets only take into account the achievable moment set of the control effectors, they do not assess the required moment set to fulfill the aircraft mission requirements. This paper proposes to calculate a corresponding required moment set (RMS) which defines a set of moments sufficient for fulfilling aircraft controllability requirements in the mission flight envelope. The paper applies the required moment set approach to a nonlinear simulation model of an electric vertical take off vehicle (eVTOL) transition drone in hover. By comparing the required moment set to the AMS of the aircraft model, moment set margins are derived and used to assess the controllability of the considered aircraft. The results indicate that the combined evaluation directly identifies critical moment channels and margins, which is advantageous when compared to a pure AMS-based evaluation. The proposed approach enables the execution of simulation-based assessments in aircraft design and flight control development. In the early stages of aircraft design, required moment sets can support sizing, positioning and tilting of control effectors (e.g., propulsive elements) to fit the AMS to the actual required force and moment set for the specific system.

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Section: Underlying Aircraft Simulation Modelmentioning

confidence: 99%

Required Moment Sets: Enhanced Controllability Analysis for Nonlinear Aircraft Models

et al. 2021

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“…Despite "wing-rock" generally not being dangerous, it is advisable to examine it more thoroughly. Studying the dynamics of this motion was attempted in numerous research work (for example: [10,[55][56][57][58][59][60]. All of the quoted work adopted quasi-static aerodynamic aircraft characteristics or presented different identification methods.…”

Section: 1"wing Rock" Oscillation Simulationmentioning

confidence: 99%

Bifurcation Flight Dynamic Analysis of a Strake-Wing Micro Aerial Vehicle

et al. 2021

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Non-linear phenomena are particularly important in -flight dynamics of micro-class unmanned aerial vehicles. Susceptibility to atmospheric turbulence and high manoeuvrability of such aircraft under critical flight conditions cover non-linear aerodynamics and inertia coupling. The theory of dynamical systems provides methodology for studying systems of non-linear ordinary differential equations. The bifurcation theory forms part of this theory and deals with stability changes leading to qualitatively different system responses. These changes are called bifurcations. There is a number of papers, the authors of which applied the bifurcation theory for analysing aircraft flight dynamics. This article analyses the dynamics of critical micro aerial vehicle flight regimes. The flight dynamics under such conditions is highly non-linear, therefore the bifurcation theory can be applied in the course of the analysis. The application of the theory of dynamical systems enabled predicting the nature of micro aerial vehicle motion instability caused by bifurcations and analysing the post-bifurcation microdrone motion. This article presents the application of bifurcation analysis, complemented with time-domain simulations, to understand the open-loop dynamics of strake-wing micro aerial vehicle model by identifying the attractors of the dynamic system that manages upset behaviour. A number of factors have been identified to cause potential critical states, including non-oscillating spirals and oscillatory spins. The analysis shows that these spirals and spins are connected in a one-parameter space and that due to improper operation of the autopilot on the spiral, it is possible to enter the oscillatory spin.

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“…Reference [12] build a general parametric flight dynamics model which can be used for online identification purpose in the three flight modes of tiltrotor aircraft (i.e., helicopter mode, conversion mode, and fixed-wing mode) is developed, and an unideal noise model is also introduced in order to minimize the parameter identification error caused by measurement noise. It can be seen that with the development of system identification, the research on identifying the stability derivative, maneuverability derivative and linear model of tilt rotor aircraft through flight data is also developing rapidly in references [13][14][15]; the modified blade element analysis theory is used to model the rotor, and the modified momentum theory is used to calculate the induced velocity in reference [16]. The model built in reference [17] considers the variation of each blade's flapping due to the elasticity of the blades.…”

Section: Introductionmentioning

confidence: 99%

Mathematical Modeling and Stability Analysis of Tiltrotor Aircraft

Sheng

Zhang

Xiang

2022

Drones

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The key problem in the development process of a tiltrotor is its mathematical modeling. Regarding that, this paper proposes a dividing modeling method which divides a tiltrotor into five parts (rotor, wing, fuselage, horizontal tail, and vertical fin) and to develop aerodynamic models for each of them. In that way, force and moment generated by each part are obtained. Then by blade element theory, we develop the rotor’s dynamic model and rotor flapping angle expression; by mature lifting line theory, the build dynamic models of the wings, fuselage, horizontal tail and vertical fin and the rotors’ dynamic interference on wings, as well as nacelle tilt’s variation against center of gravity and moment of inertia, are taken into account. In MATLAB/Simulink simulation environment, a non-linear tiltrotor simulation model is built, Trim command is applied to trim the tiltrotor, and the XV-15 tiltrotor is taken as an example to validate rationality of the model developed. In the end, the non-linear simulation model is linearized to obtain a state-space matrix, and thus the stability analysis of the tiltrotor is performed.

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Multi-Axis Inputs for Identification of a Reconfigurable Fixed-Wing UAV

Cited by 16 publications

References 34 publications

Required Moment Sets: Enhanced Controllability Analysis for Nonlinear Aircraft Models

Required Moment Sets: Enhanced Controllability Analysis for Nonlinear Aircraft Models

Bifurcation Flight Dynamic Analysis of a Strake-Wing Micro Aerial Vehicle

Mathematical Modeling and Stability Analysis of Tiltrotor Aircraft

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