Application of improved active disturbance rejection control algorithm in tilt quad rotor

Wang, Zhigang; Zhao, Hong; Duan, Dengyan; Jiao, Yuanyang; Li, Jianbo

doi:10.1016/j.cja.2020.01.002

Cited by 32 publications

(9 citation statements)

References 6 publications

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“…Due to its small size, low flying speed, low weight and moment of inertia, the micro-aircraft has a weak ability to resist air disturbances. The conventional proportionalintegral-derivative (PID) control method of UAVs is no longer applicable [21], [22], [22]- [26]. Intelligent flight control methods must be established according to different types of micro-aircraft.…”

Section: Anti-interference Stabilization Techniquementioning

confidence: 99%

The Application of Micro Coaxial Rotorcraft in Warfare: An Overview, Key Technologies, and Warfare Scenarios

Wang¹,

Liu²,

Cui³

et al. 2022

IEEE Access

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The mode of future wars is mainly local wars and regional conflicts. This style of war is characterized by unpredictability and instability, which can happen anytime and anywhere. Once it happens, the battlefield is vast, short-range and fast-changing. In order to adapt to the characteristics of this kind of warfare, simple equipment and short reaction time have become two important factors in selecting weapons. Coaxial rotorcraft has been widely studied and applied in future wars due to its convenient carrying, strong environmental adaptability, and rich load capacity. This paper conducts an overview of the Coaxial rotorcraft. Furthermore, we also identify its key technologies, warfare scenarios and future directions. We anticipate that this survey can shed new light on the coaxial rotorcraft systems. Micro aerial vehicles, coaxial, rotorcraft, warfare, application. INDEX TERMS

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Section: Anti-interference Stabilization Techniquementioning

confidence: 99%

The Application of Micro Coaxial Rotorcraft in Warfare: An Overview, Key Technologies, and Warfare Scenarios

Wang¹,

Liu²,

Cui³

et al. 2022

IEEE Access

Self Cite

View full text Add to dashboard Cite

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“…is a modeled nonlinear dynamic system and ω i is the unmodeled dynamic system including external interference, modeling error, and other factors [14,15]. b 1 is the control input gain from the deflection angle of the aileron angle to roll angular acceleration and b 2 is the control input gain from the deflection angle of the elevator angle to pitch angular acceleration.Cl δa is the coefficient of the rolling moment, while Cm δe is the coefficient of pitching moment [16].…”

Section: Extended State Observer Equationmentioning

confidence: 99%

Modeling and Design of an Aircraft-Mode Controller for a Fixed-Wing VTOL UAV

Zhao

You

2021

Mathematical Problems in Engineering

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Vertical takeoff and landing (VTOL) is an essential feature of unmanned aerial vehicles (UAVs). On the one hand, VTOL can expand and enhance the applications of UAVs; yet, on the other hand, it makes the design of control systems for UAVs more complicated. The most challenging demand in designing the control system is to achieve satisfactory response sharpness of fixed-wing UAVs to control commands and ensure that the aircraft mode channels are effectively decoupled. In this work, a six-degree-of-freedom (6-DoF) model with forces and moments is established based on the aerodynamic analysis, which is carried out through computational fluid dynamics (CFD) numerical simulation. The improved proportional derivative (PD) controller based on the extended state observer (ESO) is proposed to design the inner-loop attitude control, which increases the anti-interference ability for internal and external uncertainty of the UAV system. The motion equations of the UAV are established and divided into independent components of longitudinal and lateral motion to design the outer loop control law under minor disturbance conditions. A total energy control system (TECS) for the longitudinal height channel is proposed, which separates speed control and track control. L1 nonlinear path tracking guidance algorithm is used for lateral trajectory tracking so as to improve curve tracking ability and wind resistance. Effectiveness of this approach is proved by actual flight experiment data. Finally, a controller based on angular velocity control is designed to prevent the attitude and head reference system (AHRS) from malfunctioning. Its effectiveness is verified by the response test of the control system.

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“…18,19 The change of rotor disk angle will affect the aerodynamic characteristics of the aircraft, and also affect the flight control and RCS level. 5,20 Scattering characteristics enhancement technology is used to simulate the radar cross section of the rotor target, and the related results are analyzed and discussed. [21][22][23] In view of the fact that the influence of the propeller hub on the noise and aerodynamics of the rotor is significantly smaller than its influence on the radar stealth, 5,9,18 simple appearance and compact structure are becoming more and more important for the stealth design of the hub.…”

Section: Introductionmentioning

confidence: 99%

Blunt hub affecting the radar cross section of rotor based on dynamic scattering method

Zhou

Huang

Chen

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to study the radar characteristics of blunt-hub rotor, a dynamic scattering method (DSM) based on physical optics and physical theory of diffraction is presented. Important influencing factors are analyzed and discussed, including rotor disk inclination, azimuth, elevation angle, and radar wave frequency. The radar cross section (RCS) of the blunt-hub rotor is used for comparison with conventional-hub rotor and sharp-hub rotor. The RCS performance of the blunt-hub rotor at different radar wave frequencies is close to that of the sharp-hub rotor. At larger positive elevation angles, the RCS∼azimuth performance of the blunt-hub rotor is not as good as the other two rotors, while the RCS performance of the blunt-hub rotor has an advantage under the larger negative elevation angle and the inclination of the rotor disk. The presented DSM is feasible and effective for learning the electromagnetic scattering characteristics of the blunt-hub rotor.

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Application of improved active disturbance rejection control algorithm in tilt quad rotor

Cited by 32 publications

References 6 publications

The Application of Micro Coaxial Rotorcraft in Warfare: An Overview, Key Technologies, and Warfare Scenarios

The Application of Micro Coaxial Rotorcraft in Warfare: An Overview, Key Technologies, and Warfare Scenarios

Modeling and Design of an Aircraft-Mode Controller for a Fixed-Wing VTOL UAV

Blunt hub affecting the radar cross section of rotor based on dynamic scattering method

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