Modelling, analysis and experimental study of the prop-rotor of vertical/short-take-off and landing aircraft

Yang, Xiao; Wang, Xiangyang; Zhu, Jihong; Yan, Wenhui

doi:10.1177/09544100211070157

Cited by 4 publications

(3 citation statements)

References 14 publications

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“…The relationship between yaw inflow angle and propeller thrust azimuth change was accurately predicted by using CFD methods. Yang X [7] et al established a fast computational procedure based on the BET model to predict the propeller performance of a V/STOL aircraft during hovering, cruising, and transitional states. Qu Yuchi [8] et al derived the relationship between 1P load and measured strain by the propeller strain test method and verified it experimentally.…”

Section: Introductionmentioning

confidence: 99%

Numerical Calculation of 1P Aerodynamic Loads on Aviation Propellers

Tian,

Yan,

Zhang

2024

J. Phys.: Conf. Ser.

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To accurately predict the 1P aerodynamic loads of aviation propellers, this paper established a mathematical model of aviation propeller 1P aerodynamic loads based on the coupling method of blade element theory and momentum theory. Correction methods such as the Prandtl tip correction method and the propeller root correction method were implemented to further improve calculation accuracy. A 1P aerodynamic load calculation procedure was developed based on the mathematical model by using the Matlab software. 1P aerodynamic loads of a three-blade propeller were predicted for three different angles including 3 °, 9 °, and 12°. The numerical calculation results show that the calculated aerodynamic characteristic parameters of individual propeller blades obtained based on the propeller 1P aerodynamic load mathematical model deviate less than 6% from the CFD simulation results, and regular periodic pulsations are observed. The numerical calculations in this paper show that the propeller 1P aerodynamic load calculation procedure developed based on this model can accurately predict the propeller 1P aerodynamic load, which can provide some reference for the study of aviation propeller aerodynamic characteristics.

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Section: Introductionmentioning

confidence: 99%

Numerical Calculation of 1P Aerodynamic Loads on Aviation Propellers

Tian,

Yan,

Zhang

2024

J. Phys.: Conf. Ser.

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“…Khan and Nahon [16] developed a physics-based model for UAV propellers that was able to predict all aerodynamic forces and moments in any general forward flight condition such as no flow, pure axial flow, and pure side flow. Yang et al [17] developed a fast computational procedure based on the blade element theory (BET) to predict the propeller characteristics of a vertical/short take-off and landing (V/STOL) aircraft during hovering, cruising, and transitional states. Zhang et al [18] used the strain method to directly measure the 1P load at the engine propeller shaft, and obtained the distribution of the propeller shaft 1P load under different flight conditions through experiments.…”

Section: Introductionmentioning

confidence: 99%

Research on the Calculation Method of Propeller 1P Loads Based on the Blade Element Momentum Theory

Yan,

Tian,

Zhou

et al. 2024

Aerospace

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Aircraft propellers produce relatively large in-plane loads, called propeller 1P loads, during maneuvers such as turning, diving, and lifting, and these loads can negatively affect the flight and control of the aircraft. In order to study the change rule of 1P aerodynamic loads, in this paper, a mathematical model of the propeller 1P aerodynamic loads has been developed based on the blade element momentum theory. This mathematical model was then corrected using the Pitt–Peters incoming flow correction method, the Prandtl tip correction method, and the propeller root flow correction method. Based on this mathematical model, a calculation procedure for the propeller 1P aerodynamic loads was developed using MATLAB software, and the accuracy of the procedure was verified by comparing the results with CFD simulation results. Numerical simulations show that the results calculated based on the proposed mathematical model for the coefficients of thrust, power, bending moment, and the tangential force of the propeller have an error of less than ±6.00% compared to the CFD simulation results. For a small inflow angle, the coefficients of bending moment and tangential force of the whole propeller fluctuate in a small range. But, as the inflow angle increases, the fluctuation range of the aerodynamic characteristic parameters of the propeller increases and the fluctuation becomes more complicated. Through numerical calculations, it has been shown that the mathematical model presented herein is reliable and accurate. In addition, it greatly shortens the calculation time and improves the calculation efficiency. It is expected that the proposed model can provide a certain help for the strength design of the propeller structure and the study of the aerodynamic performance of the whole aircraft.

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“…To study aerodynamics and design aircrafts, wind tunnels, especially the continuous transonic wind tunnel (CTWT), have become indispensable. Over the past two decades, the research and practical application of wind tunnels have received increasing attention, as they are widely applied in many fields based on aerodynamic theories [1,2] and in the design of many artifact including bridges [3], buildings [4], trains [5] and aircrafts [6][7][8]. It should be especially noted that wind tunnel experimentation has great significance for wind farm research, as it can help to model the inter-farm cluster interaction of the wind power base [9].…”

Section: Introductionmentioning

confidence: 99%

Mach Number Prediction for 0.6 m and 2.4 m Continuous Transonic Wind Tunnels

2023

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With the development of the design technology, more and more advanced and diverse wind tunnels have been constructed to match complex requirements. However, it is hard to design a precise physical model of a wind tunnel that can be controlled. In addition, if a new wind tunnel is designed, the experimental data may be insufficient to build a controlling model. This article reports research on the following two models: (1) for a 0.6 m continuous transonic wind tunnel supported by a large amount of historical data, the false nearest neighbor (FNN) algorithm was adopted to calculate the order of the input variables, and the nonlinear auto-regressive model with the exogenous inputs–backpropagation network (NARX-BP) was proposed to build its Mach number prediction model; (2) for a new 2.4 m continuous transonic wind tunnel with only a small amount of experimental data, the method of model migration, the input and output slope/bias correction–particle swarm optimization (IOSBC-PSO) algorithm, was developed to convert the old model of the 0.6 m wind tunnel into the new model of the 2.4 m wind tunnel, so that the new Mach number prediction could be conducted. Through simulation experiments, it was found that by introducing the NARX-BP algorithm to build the Mach number prediction model, the root-mean-square error (RMSE) of the model decreased by 44.93–77.90%, and the maximum deviation (MD) decreased by 64.05–85.32% compared to the BP model. The performance of the IOSBC-PSO migration model was also better than that of the non-migration model, as evidenced by the 82.06% decrease of the RMSE value and the 78.25% decrease of the MD value. The experiments showed the effectiveness of the proposed strategy.

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Modelling, analysis and experimental study of the prop-rotor of vertical/short-take-off and landing aircraft

Cited by 4 publications

References 14 publications

Numerical Calculation of 1P Aerodynamic Loads on Aviation Propellers

Numerical Calculation of 1P Aerodynamic Loads on Aviation Propellers

Research on the Calculation Method of Propeller 1P Loads Based on the Blade Element Momentum Theory

Mach Number Prediction for 0.6 m and 2.4 m Continuous Transonic Wind Tunnels

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