Trimming Analysis Method of Quad Tilt Rotor Based on Aerodynamic Interference Model

Wang, Zhigang; Wang, Qiannan; Yu, Haitao; Duan, Dengyan; Ding, Zhiwei; Li, Jianbo

doi:10.2514/1.c035943

Cited by 10 publications

(4 citation statements)

References 27 publications

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“…The inner segment employs the DBLN-526 double-blunted airfoil, the middle segment the SC1210-R8 airfoil, and the outer segment the SSCA09 airfoil [34]. The aerodynamic coefficients of the airfoil are pre-calculated using a hardware-accelerated LBM method [35] and formed into C81 tables, integrated into the coaxial rigid rotor aerodynamic model described earlier. The specific distribution of airfoils is shown in Table 1.…”

Section: Optimization 31 Design Parametersmentioning

confidence: 99%

An rVPM-Based Aerodynamic Hybrid Optimization Method for Coaxial Rotor with Differentiated Upper and Lower Blades in Both Hover and High-Speed Cruising States

Ding,

Duan,

Zhang

et al. 2024

Aerospace

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To enhance the performance of rigid coaxial rotors across both hovering and high-speed cruising conditions, this study develops a novel aerodynamic optimization method that differentiates between the upper and lower rotors. Utilizing the lifting line and reformulated viscous vortex particle method (rVPM), this approach models the complex wake fields of coaxial rotors and accurately assesses the aerodynamic loads on the blades. The optimization of geometric properties such as planform configuration and nonlinear twist is conducted through an innovative solver that integrates simulated annealing with the Nelder–Mead algorithm, ensuring both rapid and comprehensive optimization results. Comparative analyses demonstrate that these tailored geometric adjustments significantly enhance efficiency in both operational states, surpassing traditional methods. This research provides a strategic framework for addressing the varied aerodynamic challenges presented by different flight states in coaxial rotor design.

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Section: Optimization 31 Design Parametersmentioning

confidence: 99%

An rVPM-Based Aerodynamic Hybrid Optimization Method for Coaxial Rotor with Differentiated Upper and Lower Blades in Both Hover and High-Speed Cruising States

Ding,

Duan,

Zhang

et al. 2024

Aerospace

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“…They are given by Eqs. ( 7) and (8). where F Lw1/Lw2 are front/rear wing lifts, F Dw1/Dw2 are drags, F Lb and F Db are lift and drag of the body, T 1−4 are thrusts generated by the propellers, and F f1−f4 are flaperon forces.…”

Section: Mathematical System Model a Dynamical Model For Quad Tilt-wing Uavmentioning

confidence: 99%

“…When the angles are 90 • , the QTW-UAV cruises with a rotary-wing mode (i.e., behaves as a multicopter). Rotating wing and rotor as a single piece avoids the impinging of the propeller slipstream on wings that reduces the thrust in the hover [8].…”

Section: Introductionmentioning

confidence: 99%

On Structural Parameter Optimization Method for Quad Tilt-Wing UAV Based on Indirect Size Estimation of Domain of Attraction

Yamaguchi

Hara

2022

IEEE Access

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To deal with the flexibility in the electric aircraft design, this study develops a structural parameter optimization method. The quad tilt-wing aircraft exhibits rotary-wing flight and fixed-wing flight modes by tilting its wings. This study focuses on the domain of attraction, which is a class of state vectors that converge to a static equilibrium point after infinite time. The method indirectly estimates the size of domain of attraction of an aircraft by calculating the radius of a sphere that is encompassed by the domain. In addition, after investigating the relationship between change in structural parameters and the size of the domain of attraction, the structural parameters that maximize the size of the domain are surveyed. The effectiveness of the proposed method is demonstrated for the optimization of the quad tilt-wing aircraft. The quad tilt-wing aircraft exhibits rotary-wing flight and fixed-wing flight modes by tilting its wings. As the characteristics of the dynamics of the quad tilt-wing aircraft demonstrate a significant nonlinear change depending on the tilt angle of the wing, we propose a method to optimize the structural parameters for an easy control of the aircraft. Simulation results show that the optimization scheme identifies the parameters that enable the aircraft to perform agile control to address a disturbance moment. Further, although the same controller is used in the original and optimized aircraft, the optimized aircraft can handle a disturbance in a shorter time when compared with the original aircraft.

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“…Unmanned aerial vehicle (UAV) technology has been advancing steadily along with science and technology's constant advancement, and the use of UAVs in agriculture has been growing recently (Zhu et al, 2020). Due to its straightforward design, excellent stability, and large load capacity, the hexacopter unmanned aerial vehicle (HUAV) is one type of UAV that is frequently utilized in the agricultural industry (Wang et al, 2021). Therefore, analyzing and studying the functionally integrated design (FID) of hexacopter agricultural unmanned aerial vehicle (HAUAV) and its appearance aerodynamic characteristics (AC).…”

Section: Introductionmentioning

confidence: 99%

Functional integration design and aerodynamic characterization of a hexacopter agricultural unmanned aerial vehicle based on its appearance

Liu

2024

Front. Mech. Eng.

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Introduction: As an advanced agricultural technology equipment, the functional integration design and appearance aerodynamic characteristics of hexacopter agricultural UAV are significant for improving the efficiency of agricultural production.Methods: Firstly, the study carried out the functional integration design of the hexacopter agricultural UAV, and completed the matching analysis and selection of the relevant components of the power system. Then, the numerical simulation method of computational fluid dynamics was used to analyze the aerodynamic characteristics of the UAV. Finally, the role of different propeller pitch on important parameters such as lift and range time of the UAV was verified.Results and discussion: The results showed that in the XY section of the UAV, namely, the surface parallel to the flight direction, the areas with high streamline velocity were mainly concentrated at the intersection of the airflow with the landing gear and the motor. The streamlines in the front of the UAV were tightly and neatly distributed, while those in the rear were sparser. The motor force efficiencies of the UAVs with different propeller pitches ranged from 7.05 to 7.25 g/w. At a flight speed of 5 m/s, the motor force effect of the UAV with a pitch of 260 mm reached 7.25 g/w, which was the highest value among all models. Meanwhile, it had the longest endurance time of 19.14 min, indicating the best performance. The results suggested that it not only promoted the modernization of agricultural UAVs but also effectively enhanced the efficiency of agricultural production.

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Trimming Analysis Method of Quad Tilt Rotor Based on Aerodynamic Interference Model

Cited by 10 publications

References 27 publications

An rVPM-Based Aerodynamic Hybrid Optimization Method for Coaxial Rotor with Differentiated Upper and Lower Blades in Both Hover and High-Speed Cruising States

An rVPM-Based Aerodynamic Hybrid Optimization Method for Coaxial Rotor with Differentiated Upper and Lower Blades in Both Hover and High-Speed Cruising States

On Structural Parameter Optimization Method for Quad Tilt-Wing UAV Based on Indirect Size Estimation of Domain of Attraction

Functional integration design and aerodynamic characterization of a hexacopter agricultural unmanned aerial vehicle based on its appearance

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