Relative Controllability Evaluation of Mass-Actuated Airplane

Erturk, Sukru Akif; Dogan, Atilla

doi:10.2514/1.g002858

Cited by 12 publications

(5 citation statements)

References 35 publications

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“…Equation (25) shows that the position of the MAUAV relative to the ground runway during the approach, glide slope, and flare is affected by the speed of vehicle. Considering that the ground speed of the MAUAV during landing with low wind disturbances mainly depends on the forward velocity u, it is necessary to control the forward velocity to make the MAUAV land efficiently and safely.…”

Section: Forward Velocity Controllermentioning

confidence: 99%

“…In the longitudinal plane, the pitch angle is controlled to ensure that the MAUAV can track the altitude trajectory for the three processes of approach, glide slope, and flare. From Equation (25), we can know that the altitude of the MAUAV relative to the ground can be expressed as…”

Section: Altitude Controllermentioning

confidence: 99%

“…It is not difficult to find that the above control methods are all applied to fixed-wing UAVs driven by ailerons. For moving-mass actuated fixed-wing UAVs, many related studies [22][23][24][25] have been carried out by Erturk et al Based on dynamics analysis and simulation tests of MAUAVs under different flight conditions, they pointed out that the moving-mass scheme can reduce fuel consumption to some extent since this method is able to eliminate the drag generated by aerodynamic surface deflection. In [16], authors concluded that the controllability of moving-mass control is similar or higher than that with aerodynamic surface solutions when the UAV is flying at low speeds.…”

Section: Introductionmentioning

confidence: 99%

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Auto-Landing of Moving-Mass Actuated Unmanned Aerial Vehicles Based on Linear Active Disturbance Rejection Control

Zheng,

Neusypin,

Selezneva

2023

Drones

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Unlike the roll motion of the unmanned aerial vehicle (UAV) controlled by the ailerons, the moving-mass actuated unmanned aerial vehicle (MAUAV) uses the motion of the mass block inside the wing to generate the roll moment. The light weight and severe coupling of lateral and longitudinal motion of this type of small UAV make its landing control a challenging task. Considering the above problems, the dynamic models of MAUAV are first established. Then, forward velocity, altitude, attitude, and moving-mass position controllers are designed separately to make the MAUAV track a given path during the landing process. Linear active disturbance rejection control (LADRC) is introduced in the design process of all four controllers, compensating for unknown disturbances in the system. Simulation results show that the proposed control scheme can achieve fast and accurate tracking of forward velocity and flight trajectory commands with good robustness to model uncertainties.

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Section: Forward Velocity Controllermentioning

confidence: 99%

Section: Altitude Controllermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Auto-Landing of Moving-Mass Actuated Unmanned Aerial Vehicles Based on Linear Active Disturbance Rejection Control

Zheng,

Neusypin,

Selezneva

2023

Drones

View full text Add to dashboard Cite

show abstract

“…Moving mass control essentially solves the surface ablation and aerodynamic shape keeping problems of ACS, and addresses the fuel limitation and side jet interaction flow shortcomings of RCS, thus becoming a more suitable attitude control technique for MaRVs. 1,2 Additionally, MMC has also been successfully demonstrated in unmanned aerial vehicles, 3 satellites, 4 underwater vehicles, 5 airships, 6 Mars landers, 7 and so on.…”

Section: Introductionmentioning

confidence: 99%

Adaptive coupled attitude-servo control for moving mass flight vehicles with high-mass-ratio

Liu

Zhou

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Moving mass flight vehicles (MMFVs) with high-mass-ratio suffer from a more severe nonlinear attitude-servo coupling than the traditional configurations that are under particle moving mass hypothesis. Therefore, the coupled attitude-servo control problem is investigated in this paper, and an adaptive backstepping sliding mode controller with extended state observers and neural-networks (ABSMC-ENN) is proposed. Based on the formulated control model with strict-feedback form, a sliding mode control law (SMC) with exponential reaching rate and a nonsingular terminal sliding mode control law (NTSMC) are combined to perform the fast and robust tracking of the command angle-of-attack. Considering the disturbances and uncertainties existing in the coupled dynamics, two nonlinear extended state observers (ESOs) are utilized to estimate the total disturbances online for compensation. To further enhance the adaptiveness and dynamic response performances of the controller in various flight conditions, two radial basis function neural networks (RBFNNs) are exploited to optimize the switching gains of the controller in real-time with performance indexes being the functions of tracking errors. Closed-loop stability of the whole system is proved via Lyapunov methodology. Comparison simulation studies considering multiple disturbances, various flight conditions, and different controllers successfully demonstrate the superiority of the ABSMC-ENN in robustness and adaptiveness.

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“…[2][3][4][5][6][7][8] Configuration of moving mass is one of the inevitable issues during the research process of moving mass flight vehicles, and numerous studies have successfully demonstrated the feasibility and outstanding performance of the configurations with two or three moving masses. [9][10][11][12][13][14] However, with the gradual transition from theoretical research to engineering application, the design of moving mass configuration not only needs to meet the requirements of maneuvering performance but also should be considered in combination with the difficulty of practical engineering implementation. Therefore, a novel configuration of moving mass was proposed in articles, [15][16][17][18] which is characterized by a pitch-control moving mass with large mass ratio.…”

Section: Introductionmentioning

confidence: 99%

Bifurcation analysis for a novel flight vehicle with pitch-control single moving mass

Liu

Gao

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Moving mass flight vehicle is a strongly nonlinear system under high speed flying conditions. The system attitude dynamics becomes even more complex due to the coupling between the internal moving mass with large mass ratio and the vehicle body. This article investigates the open-loop nonlinear dynamics of a novel flight vehicle with pitch-control single moving mass from the prospective of bifurcation theory and continuation methods. Of particular interest is the influence of moving mass parameters on the number of system equilibrium points, stability of equilibrium curves, bifurcation characteristics, and the longitudinal static stability. Numerical results reveal the bifurcation phenomena existing in the proposed flight vehicle; the generated bifurcation diagrams illustrate that the multiple sets of limit points and Hopf points divide the moving mass parameter space into different regions with different values and types of stability, thus indicating the significant role of the moving mass parameters in the system nonlinear dynamics. Finally, a design strategy for the moving mass parameters is concluded based on the bifurcation analysis results.

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Relative Controllability Evaluation of Mass-Actuated Airplane

Cited by 12 publications

References 35 publications

Auto-Landing of Moving-Mass Actuated Unmanned Aerial Vehicles Based on Linear Active Disturbance Rejection Control

Auto-Landing of Moving-Mass Actuated Unmanned Aerial Vehicles Based on Linear Active Disturbance Rejection Control

Adaptive coupled attitude-servo control for moving mass flight vehicles with high-mass-ratio

Bifurcation analysis for a novel flight vehicle with pitch-control single moving mass

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