Tri-Copter UAV With Individually Tilted Main Wings for Flight Maneuvers

Nam, Kyung-Jae; Joung, Joosang; Har, Dongsoo

doi:10.1109/access.2020.2978578

Cited by 10 publications

(9 citation statements)

References 45 publications

(56 reference statements)

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“…Lastly, the results verify the efficiency of the suggested algorithm. In another recent research on fixedwing aircraft, reference [17] offers a new design of the aerial vehicle with independently tilt wings for different flight movements. Contrary to traditional tilt wing aircraft, this study attains the thrust vectoring and direction control of the aircraft by tilting the main wings separately.…”

Section: State Of the Artmentioning

confidence: 99%

Guidance, Navigation, and Control for Fixed-Wing UAV

Israr

Alkhammash

Hadjouni

2021

Mathematical Problems in Engineering

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The purpose of this paper is to develop a fixed-wing aircraft that has the abilities of both vertical take-off (VTOL) and a fixed-wing aircraft. To achieve this goal, a prototype of a fixed-wing gyroplane with two propellers is developed and a rotor can maneuver like a drone and also has the ability of vertical take-off and landing similar to a helicopter. This study provides guidance, navigation, and control algorithm for the gyrocopter. Firstly, this study describes the dynamics of the fixed-wing aircraft and its control inputs, i.e., throttle, blade pitch, and thrust vectors. Secondly, the inflow velocity, the forces acting on the rotor blade, and the factors affecting the rotor speed are analyzed. Afterward, the mathematical models of the rotor, dual engines, wings, and vertical and horizontal tails are presented. Later, the flight control strategy using a global processing system (GPS) module is designed. The parameters that are examined are attitude, speed, altitude, turn, and take-off control. Lastly, hardware in the loop (HWIL) based simulations proves the effectiveness and robustness of the navigation guidance and control mechanism. The simulations confirm that the proposed novel mechanism is robust and satisfies mission requirements. The gyrocopter remains stable during the whole flight and maneuvers the designated path efficiently.

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Section: State Of the Artmentioning

confidence: 99%

Guidance, Navigation, and Control for Fixed-Wing UAV

Israr

Alkhammash

Hadjouni

2021

Mathematical Problems in Engineering

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“…Because they can switch between two distinct flight modes, hybrid UAVs are quickly becoming increasingly popular. Several researchers were explored the enhancement of the hybrid VTOL UAV design [10][11][12][13][14][15][16][17][18][19][20][21][22]. A wingtip designs for a Quad+Tilt configuration with different control principles were proposed and gain of 3% improvement in cruise endurance for a 5 kg Quad+Tilt UAV [12].…”

Section: Introductionmentioning

confidence: 99%

“…A wingtip designs for a Quad+Tilt configuration with different control principles were proposed and gain of 3% improvement in cruise endurance for a 5 kg Quad+Tilt UAV [12]. There are also several studies related to tilt concept that improve in attitude stabilization [17] and the effectiveness of the flight control system [18][19][20] The designs enhancement was conducted may focusing on several factors as well such as wind condition during landing and take-off [11] aerodynamics load at the "tail-aft on booms" shaped configuration [14] and morphing wing design [10,15,16]. The new concept of tri-copters produces better performance in term reduce mechanical requirement [21] control surface flight performance [19], and employed less components [22].…”

Section: Introductionmentioning

confidence: 99%

Investigation of Empennage Location Effect to the Unmanned Aerial Vehicle (UAV) Structure Characteristic

Farid Danial Norazman,

Ahmad Hamdan Ariffin,

Mohd Rahmat Firman Sahifulddin

et al. 2024

ARAM

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Over the past few decades, unmanned aerial vehicles, commonly known as UAVs, have been widely used in a number of consumer and military applications, such as surveillance, tracking, monitoring, and aerial photography. Fixed-wing and rotary UAVs are the two primary categories in UAV. Interestingly, the hybridization of fixed-wing and rotary UAV gives better performance in terms of energy consumption and the needs of runaway. Designing new hybrid fixed wing-rotary UAV or hybrid vertical take-off and landing (VTOL) is challenging especially to identify the critical location in the UAV and material selection. Therefore, the objective of this research is to study the effect of empennage location and material selection on the structural strength of a hybrid VTOL UAV. The SolidWorks software was employed to design a 3D model of the UAV with different empennage locations, as well as perform a simulation of the structural strength of fibre glass, carbon fibre and kenaf for the hybrid VTOL UAV. The simulation analysis presents stress (Von Mises). The results show that the fibre glass (4.342 N/m2) at top empennage gives the best performance as compared to other parameters. In conclusion, this study is necessary to give a better picture of structural strength of composite materials and best design location in hybrid VTOL UAV for future research.

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“…The tail servo not only makes it difficult to consider the control of this object but also provides opportunities for better control during dynamic movements. In a number of papers, including [16], the authors have considered the control of the chosen design but have not considered the choice of controller settings depending on the mission to be performed by the UAV. Most of the research conducted does not focus on using the tricopter to perform a specific task but only on experiments testing the correctness of derived models [10].…”

Section: Introductionmentioning

confidence: 99%

Optimal Control for a Three-Rotor Unmanned Aerial Vehicle in Programmed Flights

Salwa,

Krzysztofik

2023

Applied Sciences

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In this study, we propose a new approach to selecting PID controller parameters for a UAV tricopter during programmed flights. The approach uses optimization techniques to determine the optimal values of the PID controller parameters based on the desired performance of the UAV. The proposed method is particularly effective for repeated programmed flights in which the UAV follows a defined flight path. The use of a PID control provides a reliable and robust control system that can cope with various disturbances and uncertainties in UAV dynamics. The proposed method provides an alternative to adaptive control, which requires a significant amount of system identification and parameter tuning. The effectiveness of the proposed method has been verified in simulation studies, and the results show its ability to achieve satisfactory performance with low tracking error and fast response time. The result of the work is an improvement in control for a specific object at a specific mission. We present how the recipients can perform this procedure for their object and their mission to be able to improve the control gain in the physical controller.

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Tri-Copter UAV With Individually Tilted Main Wings for Flight Maneuvers

Cited by 10 publications

References 45 publications

Guidance, Navigation, and Control for Fixed-Wing UAV

Guidance, Navigation, and Control for Fixed-Wing UAV

Investigation of Empennage Location Effect to the Unmanned Aerial Vehicle (UAV) Structure Characteristic

Optimal Control for a Three-Rotor Unmanned Aerial Vehicle in Programmed Flights

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