Rapid design method for rotor wing of electric unmanned aerial vehicle

Abstract

The invention relates to a rapid design method of an electric unmanned aerial vehicle rotor wing, which comprises the following steps: S1, determining the overall design technical requirements of an electric propulsion unmanned aerial vehicle, including the design height H, the required pulling force Tdesign, the cruising speed V, the cruising efficiency eta and the size constraint; s2, determining a designed rated rotating speed omega and a designed diameter D of the rotor wing; s3, determining airfoil profile configuration; s4, preliminarily determining chord length distribution b (x) by adopting a statistical experience method; s5, determining torsion beta (x) distribution; s6, evaluating the performance of the rotor wing; s7, judging and calculating the relation between the tension T and the tension Tdesign required by the design; calculating a rotor force effect; according to the rotor design, complex three-dimensional shape optimization is not needed, the requirement for rotor design precision in the overall scheme demonstration stage can be met, and the requirement for rapid evaluation is met. The design method is used for rapid design, and through test data comparison and verification calculation, it is proved that the design method is reliable in calculation precision, the design period of the rotor wing is greatly shortened, and the requirements for rapid design and precision of the rotor wing are met.

Description

technical field [0001] The invention belongs to the field of rotorcraft power system design, and in particular relates to a rapid design method for an electric unmanned aerial vehicle rotor. Background technique [0002] With the gradual opening of the low-altitude field, the general aviation industry is developing rapidly. With its excellent hovering performance, rotor drones are widely used in many fields, which can effectively change the original operation mode and improve resource utilization. As the core of the vertical take-off and landing UAV power system, the rotor has a complex working flow field and is difficult to design. The conventional design method is mainly the optimization design based on the surrogate model. The calculation methods include numerical and analytical calculations. Due to the complex shape of the rotor and too many design variables, both numerical and theoretical methods have problems such as long iteration period and difficulty in convergence,...

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problems of long iterative cycle and difficult convergence of conventional rotor design methods, the present invention provides a rapid design method for electric UAV rotors, the purpose of which is to provide a rapid rotor design method in the demonstration stage of the overall scheme of rotorcraft

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