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. 2023 Jun 14;23(12):5561.
doi: 10.3390/s23125561.

Thrust Vectoring Control for Heavy UAVs, Employing a Redundant Communication System

Mohammad Sadeq Ale Isaac  1   2 , Ahmed Refaat Ragab  3   4   5 , Marco Andrés Luna  1   6 , Mohammad Mehdi Ale Eshagh Khoeini  7 , Pascual Campoy  1
Affiliations

Thrust Vectoring Control for Heavy UAVs, Employing a Redundant Communication System

Mohammad Sadeq Ale Isaac et al. Sensors (Basel). .

Abstract

Recently, various research studies have been developed to address communication sensors for Unmanned Aerial Systems (UASs). In particular, when pondering control difficulties, communication is a crucial component. To this end, strengthening a control algorithm with redundant linking sensors ensures the overall system works accurately, even if some components fail. This paper proposes a novel approach to integrate several sensors and actuators for a heavy Unmanned Aerial Vehicle (UAV). Additionally, a cutting-edge Robust Thrust Vectoring Control (RTVC) technique is designed to control various communicative modules during a flying mission and converge the attitude system to stability. The results of the study demonstrate that even though RTVC is not frequently utilized, it works as well as cascade PID controllers, particularly for multi-rotors with mounted flaps, and could be perfectly functional in UAVs powered by thermal engines to increase the autonomy since the propellers cannot be used as controller surfaces.

Keywords: UAV; sliding mode; sommunication; thrust vectoring control.

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Conflict of interest statement

The authors declare no conflict of interest.

Figures

Figure 1
Figure 1
The overall schematic of the UAV system.
Figure 2
Figure 2
The AP infrastructure and its sub-components.
Figure 3
Figure 3
The UAS infrastructure and the communication system.
Figure 4
Figure 4
Effects of the blade tip angle on the thrust generation and power consumption.
Figure 5
Figure 5
Effects of the blade numbers on the thrust generation and power consumption.
Figure 6
Figure 6
Comparison of the impact of blade number on the power, pressure drop, thrust, and power-to-weight ratio.
Figure 7
Figure 7
A simple schematic of the duct and the flap vanes installed at the exhaust.
Figure 8
Figure 8
(Realistic Simulation). The horizontal projection of the reference and actual trajectory in the presence of a random wind disturbance and a semi-circular area.
Figure 9
Figure 9
(Realistic Simulation). The horizontal projection of the reference and actual trajectory in the presence of a random wind disturbance and a rectangular area.
Figure 10
Figure 10
(Ideal Simulation). The horizontal projection of the reference and actual trajectory, in a semi-circular area, which is controlled by a cascade PID controller.
Figure 11
Figure 11
(Ideal Simulation). The horizontal projection of the reference and actual trajectory, in a rectangular area, which is controlled by a cascade PID controller.
See this image and copyright information in PMC

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