Rapid design method of electric propulsion propeller

A design method and propeller technology, applied in design optimization/simulation, electrical digital data processing, special data processing applications, etc., can solve problems such as long iteration cycle and difficulty in convergence, achieve reliable calculation accuracy, shorten design cycle, and meet fast Effect of design and precision requirements

Pending Publication Date: 2022-03-04
湖北航天飞行器研究所
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Problems solved by technology

[0004] Aiming at the problems of long iterative cycle and difficult convergence of conventional propeller design methods, the present invention provides a rapid design method fo

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  • Rapid design method of electric propulsion propeller
  • Rapid design method of electric propulsion propeller
  • Rapid design method of electric propulsion propeller

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[0068] In order to make the objects, technical solutions and advantages of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and examples. It will be appreciated that the specific embodiments described herein are intended to explain the invention and is not intended to limit the invention. Further, the technical features according to each of the various embodiments described below can be combined with each other as long as they do not constitute a collision between each other.

[0069] The propeller design method provided by the present invention mainly includes the following steps: first clarify the overall design technical requirements of the propeller; determine the design rated speed and design diameter, airfoil configuration, chord length, and torsion distribution; use the tab theory to the propeller performance evaluation; constantly adjust the design Parameters until the propeller computational thrust ...

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Abstract

The invention relates to a rapid design method of an electric propulsion propeller. The method comprises the following steps: S1, determining the overall design technical requirements of an electric propulsion unmanned aerial vehicle; s2, the designed rated rotating speed omega and the designed diameter D of the propeller are determined; 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 propeller; s7, the relation between the thrust T and the thrust Tdesign required by design is judged and calculated; s8, calculating energy consumption; according to the design method, complex three-dimensional shape optimization is not needed in the design of the propulsion propeller, only a few overall design parameters are needed to be input, the design precision requirement of the propeller in the overall scheme demonstration stage of the electric propulsion unmanned aerial vehicle can be met, and the requirement for rapid evaluation is met. Verification calculation proves that the design method is reliable in calculation precision, the design period of the propeller is greatly shortened, and the requirements for rapid design and precision of the propeller in the overall scheme demonstration stage of the electric propulsion unmanned aerial vehicle are met.

Description

technical field [0001] The invention belongs to the field of power system design of an electric unmanned aerial vehicle, and in particular relates to a rapid design method of an electric propulsion propeller. Background technique [0002] With the rise of general aviation, UAVs are used more and more widely. Whether in military or civilian fields, UAVs are mainly divided into two types: electric and oil-driven according to different power sources. Compared with oil-driven, Electric UAVs have the advantages of simple power system structure, large payload, simple operation, and environmental protection. Therefore, the existing small and medium-sized UAVs basically tend to adopt electric drive forms. As the core of the power system of the electric UAV, the propeller has a complex working flow field and is difficult to design. The conventional design method is mainly based on the optimization design of the surrogate model. The calculation methods include numerical calculation a...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F119/14
CPCG06F30/15G06F30/20G06F2119/14Y02T90/00
Inventor 裴家涛黄晓龙李康伟周子鸣张达张华君刘青许铠通
Owner 湖北航天飞行器研究所
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