Development of an unmanned tail-sitter with reconfigurable wings: U-Lion

Ang, Kevin Z. Y.; Cui, Jinqiang; Pang, Tao; Li, Kun; Wang, Kangli; Ke, Yijie; Chen, Ben M.

doi:10.1109/icca.2014.6871015

Cited by 10 publications

(7 citation statements)

References 4 publications

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“…These characteristics solve the low efficiency and short-range of failures for multi-rotor UAVs, the lengthy fixed-wing UAV take-off preparation, auxiliary equipment requirements, and various landing problems. Ang et al designed a foldable tailsitter U-lion in 2014 [12]. The wing of this U-lion could be retracted through a link mechanism, which improved the maneuverability and portability of the drone.…”

Section: Multi-objective Optimizationmentioning

confidence: 99%

“…Many studies used computational fluid dynamics (CFD) in tailsitter UAV design and aerodynamic optimization [6][7][8][9][10][11]. In 2014, Ang et al designed a foldable drone U-lion using a CFD numerical simulation to compare and analyze the lift-drag ratio and polar curve of different wings and completed the structural design and parameter optimization of the wings [12]. In 2017, Wang et al designed a four-rotor drone and analyzed the changes in the lift coefficient, torque, and polar curve of the drone with different angles of attack from 0 • to 90 • [13].…”

Section: Introductionmentioning

confidence: 99%

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Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

Yao

Liu

Han

et al. 2020

Sensors

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This study designed a vertical take-off and landing tailsitter unmanned aerial vehicle (UAV) with a long endurance time. Nine parameters of the tailsitter UAV were investigated. Using a 2k full factorial test, 512 experiments on the nine parameters were conducted at their maximum and minimum values. The time coefficient and air resistance were calculated using the computational fluid dynamics (CFD) method under different parameter combinations. The analysis of variance determined that the specific factors influencing the time coefficient and air resistance were the root chord, wingtip chord, wingspan, and sweep angle. By carrying out a central composite design (CCD) test, 25 sample points of the four particular factors were constructed. The time coefficient and air resistance were simulated under different structural parameter combinations using the CFD method. CFD simulation was verified by carrying out a wind tunnel test, and the results revealed that the aerodynamic coefficient error was less than 5%, while the air resistance error was less than 6%. The response surface methodology (RSM) for the time coefficient and air resistance was established using a genetic aggregation method. A multi-objective genetic algorithm (MOGA) was used to optimize the parameters with regard to the maximum time coefficient and minimum air resistance. The optimal structural parameters were wing root chord length at 315 mm, wingtip chord length at 182 mm, wingspan length at 1198 mm, and sweep angle at 16°. Compared with the original layout and size, the time coefficient of the new design of the tailsitter UAV improved by 19.5%, while the air resistance reduced by 34.78%. The results obtained by this study are significant for the design of tailsitter UAVs.

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Section: Multi-objective Optimizationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

Yao

Liu

Han

et al. 2020

Sensors

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“…As a consequence, differential rotational speed of right BLDC motor with respect to left BLDC motor creates roll operation described in equation (23). In case of pitch operation in equation (24), the output of the PID controller for pitch operation U θ should be commonly used to determine ω 1 , ω 2 , ω 3 . Direction of pitch operation, either nose up or nose down, is determined by the rotational speed of tail BLDC motor ω 3 relative to ω 1 , ω 2 , as shown in equation (24).…”

Section: A Control Model For Vertical Flight Modementioning

confidence: 99%

“…In case of pitch operation in equation (24), the output of the PID controller for pitch operation U θ should be commonly used to determine ω 1 , ω 2 , ω 3 . Direction of pitch operation, either nose up or nose down, is determined by the rotational speed of tail BLDC motor ω 3 relative to ω 1 , ω 2 , as shown in equation (24). For yaw operation, tilt angle of right servo motor θ 1 is 90 • − U ψ and tilt angle of left servo motor θ 2 is 90 • + U ψ , as expected.…”

Section: A Control Model For Vertical Flight Modementioning

confidence: 99%

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

2020

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A tri-copter unmanned aerial vehicle (UAV) with individually tilted main wings for various flight maneuvers is presented. In contrast to conventional tilt wing UAVs, thrust vectoring and control of the directions of main wing surfaces are attained by tilting main wings individually. Such individually tilted main wings allow more efficient maneuvers of the UAV. Even though the UAV is a tri-copter, it can compensate the reaction torque created by the tail motor by the individual control of the main wings. Few publications have appeared in the literature, dealing with tri-copter UAV with individually tilted main wings. Dynamic model of the UAV is established via the Newton-Euler formulation and effect of individual wing control is examined. The PID controller and PI controller for control of flight maneuvers are implemented and used for simulations and experiments. Results of simulations and experiments are presented for validation of flight performance of the UAV, including the roll rate 80% larger than that of the conventional UAV with ailerons as control surfaces.

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“…4 Ang, et al developed U-Lion, which has reconfigurable wings and thrust vectoring system with co-axial propeller. 5 In the second place, the tilt-rotor has mostly designed with dual tilt-rotors. Bell Helicopter successfully completed their tilt-rotor UAV development program called the Bell Eagle Eye.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Modeling and Analysis of a Single Tilt-Wing Unmanned Aerial Vehicle

Jeong

Yoon

Kim

et al. 2015

AIAA Modeling and Simulation Technologies Conference

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A single tilt-wing UAV has a new-concept hybrid configuration for adopting the advantages of both fixed-wing and rotary-wing aircraft. This paper presents a dynamic modeling and analysis of the single tilt-wing UAV which is composed of a tilted main wing, a fuselage, a tail wing, and a variable pitch propeller. The main wing can be divided into tilted and fixed section. The tilted section is located at outer wing and has an electric propulsive system at each side. The variable pitch system is used for improving control performance during vertical flight. The dynamic modeling is derived by forces and moments analysis of the UAV. Momentum theory and blade element theory are used for thrust term, and a wetted and an unwetted area are considered for the precise main wing model. The force and moment variation is considered for tilting angle change from 0 to 90 degrees: cruise to hover mode. Also, trim conditions are analyzed for each flight mode, and flight dynamic characteristics are presented through open-loop pole location with respect to trim conditions.

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Development of an unmanned tail-sitter with reconfigurable wings: U-Lion

Cited by 10 publications

References 4 publications

Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

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

Dynamic Modeling and Analysis of a Single Tilt-Wing Unmanned Aerial Vehicle

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