Attitude control of ducted fan UAV with three auxiliary rotor

This paper presents a flight control system for an organic flight array (OFA) with a new configuration consisting of multimodularized ducted-fan unmanned aerial vehicles. The OFA has a distinguished advantage of assembling or separating with respect to its missions or operational conditions because of its reconfigurable structure. Therefore, designing a controller that can be flexibly applied in each situation is necessary. First, a dynamic modeling of the OFA based on a single ducted-fan vehicle is performed. Second, the inner loop for attitude control is designed through dynamic model inversion and a PD controller. However, an adaptive control component is needed to flexibly cope with the uncertainty because the operating environment of the OFA is varied, and uncertainty exists depending on the number of modules to be assembled and disturbances. In addition, the performance of the neural network adaptive controller is verified through a numerical simulation according to two scenarios.

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Adaptive Control for Steering Engine Fault of Ducted Fan UAV

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.602-605.834 ◽

2014 ◽

Vol 602-605 ◽

pp. 834-843

Author(s):

An Huang ◽

Zhong Xi Hou

Keyword(s):

Control System ◽

Attitude Control ◽

Adaptive Controller ◽

Attitude Control System ◽

Model Reference ◽

Ducted Fan ◽

Model Reference Adaptive ◽

The Impact ◽

The Relationship ◽

Good Attitude

For the steering engine fault of ducted fan UAV that may arise during the hovering, designing adaptive controller for attitude control. First, concentrating on modeling of the hovering state of ducted fan UAV, and getting the relationship between steering engine and attitude control. Then analyzing the impact of steering engine fault on the attitude control system basing on the control model. Finally, designing model reference adaptive controller basing on the fault model, so that the ducted fan UAV can maintain good attitude control if steering engine fault occurs during the hovering. Simulation results show that when steering engine fault occurs, the model reference adaptive controller can effectively inhibit the adverse effects brought by steering engine fault, so the attitude control system has strong adaptability and robustness.

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Modelling and attitude control of novel multi-ducted-fan aerial vehicle in forward flight

International Journal of Modelling Identification and Control ◽

10.1504/ijmic.2019.10017478 ◽

2019 ◽

Vol 31 (1) ◽

pp. 81

Author(s):

Lu Lin ◽

Wanming Chen ◽

Yue Ma

Keyword(s):

Attitude Control ◽

Forward Flight ◽

Ducted Fan ◽

Aerial Vehicle

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1011 Attitude Control of Multi Ducted-fan Helicopter

The Proceedings of Conference of Chugoku-Shikoku Branch ◽

10.1299/jsmecs.2013.51._1011-1_ ◽

2013 ◽

Vol 2013.51 (0) ◽

pp. _1011-1_-_1011-2_

Author(s):

Shinji UEMURA ◽

Akitaka IMAMURA ◽

Masafumi MIWA

Keyword(s):

Attitude Control ◽

Ducted Fan

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Attitude Control for Ducted Fan UAV Based on Sliding Mode Adaptive Algorithm

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.513-517.3915 ◽

2014 ◽

Vol 513-517 ◽

pp. 3915-3918

Author(s):

Xiao Lu Ren ◽

Chang Hong Wang ◽

Guo Xing Yi

Keyword(s):

Attitude Control ◽

Control Method ◽

Sliding Mode ◽

Dynamic Performance ◽

External Disturbance ◽

Pass Filter ◽

Low Pass Filter ◽

Ducted Fan ◽

Multiple Input ◽

Low Pass

According to the complicated condition and special dynamic performance of the Ducted Fan UAV, a nonlinear multiple input and multiple output control method is designed. This method is based on the sliding mode adaptive theory. Introducing the integral term, this method can work without the derivative value of the tracked signal; even the derivative doesnt exist or cannot be got. The adaptive control can identify the uncertain parameters and external disturbance, and adjust the controllers parameters real-time. Using a low-pass filter can effectively inhibit the chattering phenomenon in sliding mode control system. The Ducted Fan UAV attitude is controlled by this method. The simulation results show that this method has strong robustness and good tracking performance.

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