Preliminary Design Method and Prototype Testing of a Novel Rotors Retractable Hybrid VTOL UAV

Xiong, Zijian; Xu, Yongfu; Wang, Zhouyang; Pian, Xuechao; Wang, Yibing

doi:10.1109/access.2021.3131565

Cited by 6 publications

(5 citation statements)

References 24 publications

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“…As 4R-UAV is not designed for a specific mission, the main goal is to design a multipurpose small-scale UAV for a range of civilian and defense applications. For the wing design parameters, Xiong [21] suggested the relationship between the wingspan range and the maximum takeoff weight. Based on Xiong's [21] work, a range of 4-6 kg maximum takeoff weight and 1.5-2.0 m wingspan were selected as the initial design parameters of the 4R-UAV.…”

Section: Investigation Methodologymentioning

confidence: 99%

“…For the wing design parameters, Xiong [21] suggested the relationship between the wingspan range and the maximum takeoff weight. Based on Xiong's [21] work, a range of 4-6 kg maximum takeoff weight and 1.5-2.0 m wingspan were selected as the initial design parameters of the 4R-UAV.…”

Section: Investigation Methodologymentioning

confidence: 99%

“…In the next step, wing surface area and lift force were evaluated. For the wing surface area, [22] and other studies [13,[21][22][23] suggested an iterative approach for the selection of cruising angle of attack and surface area. For this, the authors' previous study [19] was found to be useful, which provided an initial approximation for the wing area and expected values of C L .…”

Section: Investigation Methodologymentioning

confidence: 99%

See 2 more Smart Citations

Computational Investigations for the Feasibility of Passive Flow Control Devices for Enhanced Aerodynamics of Small-Scale UAVs

Arshad,

Kovaļčuks

2024

Aerospace

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The 4R-UAV project aims to develop aerodynamically efficient and environmentally friendly UAVs based on the 4R Circular Economy principle. In this study, the feasibility of the application of PFCDs (Passive Flow Control Devices) was investigated for the small-scale low-speed 4R-UAV wing. The application of PFCDs for small-scale UAV wings is relatively unexplored. Two PFCD types, i.e., MVGs (Micro Vortex Generators) and winglets, were considered for the investigations. In the stepwise investigations, the aerodynamic performance of the MVGs and the winglets was analyzed for the short-span 4R-UAV wing, which was developed from the aerodynamically optimized airfoil SG6043mod. MVGs enhanced the wings near stall properties (especially maximum lift coefficient) and contributed to the delayed wing stall of up to 2°. MVGs manifested the main aerodynamic advantage, which was achieved at the higher angles of attack. Winglets, on the other hand, were found to be extremely effective in cruise conditions with improved pre-stall characteristics. Extensive investigations on winglets were carried out by designing six winglet configurations for the 4R-UAV wing. Blended-type winglets performed well and enhanced pre-stall properties by decreasing the drag (up to 10%) of the wing. The main performance improvement was found in the early angles of attack. In the final step, the combined effect of the integrated PFCDs was analyzed. The final wing (integrated MVGs and winglets) also exhibited enhanced performance with nearly 6% increased lift-to-drag ratio in cruise conditions. The limited aerodynamic advantage achieved from the PFCDs in small-scale UAV applications can be useful in specific (civil or military) missions. Further verifications are planned in the future by means of experimental and flight testing.

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Section: Investigation Methodologymentioning

confidence: 99%

Section: Investigation Methodologymentioning

confidence: 99%

Section: Investigation Methodologymentioning

confidence: 99%

See 1 more Smart Citation

Computational Investigations for the Feasibility of Passive Flow Control Devices for Enhanced Aerodynamics of Small-Scale UAVs

Arshad,

Kovaļčuks

2024

Aerospace

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“…Operating a multi-copter is not optimal as its coverage is minimal, although it does not need open space for take-off and landing. The solution is a hybrid vertical take-off and landing (VTOL) UAV [8][9][10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26]. This type of UAV can take off, land vertically like a multicopter, and transition to the fixed-wing mode for flight efficiency at a safe altitude [27][28][29][30][31][32].…”

Section: Introductionmentioning

confidence: 99%

Validation of Quad Tail-sitter VTOL UAV Model in Fixed Wing Mode

Priyambodo

Majid²,

Shouran³

2023

Journal of Robotics and Control

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Vertical take-off and landing (VTOL) is a type of unmanned aerial vehicle (UAV) that is growing rapidly because its ability to take off and land anywhere in tight spaces. One type of VTOL UAV, the tail-sitter, has the best efficiency. However, besides the efficiency offered, some challenges must still be overcome, including the complexity of combining the ability to hover like a helicopter and fly horizontally like a fixed-wing aircraft. This research has two contributions: in the form of how the analytical model is generated and the tools used (specifically for the small VTOL quad tail-sitter UAV) and how to utilize off-the-shelf components for UAV empirical modeling. This research focuses on increasing the speed and accuracy of the UAV VTOL control design in fixed-wing mode. The first step is to carry out analysis and simulation. The model is analytically obtained using OpenVSP in longitudinal and lateral modes. The next step is to realize this analytical model for both the aircraft and the controls. The third step is to measure the flight characteristics of the aircraft. Based on the data recorded during flights, an empirical model is made using system identification technique. The final step is to vali-date the analytical model with the empirical model. The results show that the characteristics of the analytical mode fulfill the specified requirements and are close to the empirical model. Thus, it can be concluded that the analytical model can be implemented directly, and consequently, the VTOL UAV design and development process has been shortened.

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“…The most common classification is based on wing type, which includes two basic categories: fixed-wing and rotary-wing UAVs. More recently, flapping-wing and hybrid UAVs [1] have also gained attention in research. The choice of aircraft category primarily depends on the mission profile.…”

Section: Introductionmentioning

confidence: 99%

Heavy-Lift Multirotor Unmanned Aerial Vehicles Characterization and Sizing

Kotarski,

Piljek,

Kasać

2023

IEEE Access

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In this paper, the characterization and sizing of heavy-lift multirotor UAVs are carried out. For this purpose, the electric multirotor UAV system is briefly described, and the parameters are carefully selected encompassing a wide range of UAVs regarding size and power. In the initial phase, comprehensive experimental measurements are conducted. Through a systematic data acquisition process, a database for two series of electric propulsion units (low voltage and high voltage setups), is obtained. Using the presented identification procedure, the data is processed, and the characterization is completed in the following step. Based on experimental data, a more accurate model of aerodynamic forces and torques and electric power was obtained, compared to previous approaches. The sizing of the heavy-lift multirotor UAV, based on propulsion unit experimental characterization, was undertaken in the last step. In this research, the sizing of conventional multirotor configurations in terms of diagonal, take-off mass, hovering power, and payload capacity is shown graphically. Proposed sizing steps enable further performance analysis for system design purposes especially from the aspect of payload.INDEX TERMS Electric propulsion unit, heavy-lift multirotor, multirotor configuration, payload capacity, unmanned aerial vehicles.

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Preliminary Design Method and Prototype Testing of a Novel Rotors Retractable Hybrid VTOL UAV

Abstract: Date of publication xxxx 00, 0000, date of current version xxxx 00, 0000.

Cited by 6 publications

References 24 publications

Computational Investigations for the Feasibility of Passive Flow Control Devices for Enhanced Aerodynamics of Small-Scale UAVs

Computational Investigations for the Feasibility of Passive Flow Control Devices for Enhanced Aerodynamics of Small-Scale UAVs

Validation of Quad Tail-sitter VTOL UAV Model in Fixed Wing Mode

Heavy-Lift Multirotor Unmanned Aerial Vehicles Characterization and Sizing

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