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Pneumatic simulation analysis method for flapping-paddling-twisting flapping-wing air vehicle

A flapping-wing aircraft and simulation analysis technology, applied in the field of aerodynamic simulation analysis of "flashing-swiping-twisting" flapping-wing aircraft, can solve the problems of insufficient aerodynamic lift, low flight efficiency, etc., and achieve fast computing speed, fast and accurate flapping. The effect of moving structures

Pending Publication Date: 2022-02-15
CHANGCHUN UNIV OF TECH
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Problems solved by technology

[0003] The main purpose of the present invention is to propose a "flutter-stroke-twist" aerodynamic simulation analysis method for flapping-wing aircraft, which can solve the above-mentioned questions provide useful theoretical guidance

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  • Pneumatic simulation analysis method for flapping-paddling-twisting flapping-wing air vehicle
  • Pneumatic simulation analysis method for flapping-paddling-twisting flapping-wing air vehicle
  • Pneumatic simulation analysis method for flapping-paddling-twisting flapping-wing air vehicle

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Embodiment Construction

[0050] The embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0051] The present invention proposes an aerodynamic simulation analysis method of "flapping-swiping-twisting" flapping-wing aircraft, including three-dimensional modeling, grid division, steady-state analysis, unsteady-state analysis, and post-processing. The specific steps are as follows: figure 1 shown, including:

[0052] Step 1: Establish a three-dimensional model of the aircraft wing, and determine the calculation domain of the flow field in combination with aerodynamic theory and related empirical formulas;

[0053] Step 2: Import the 3D model of the wing and computational domain into Ansys software, and perform mesh division and fluid analysis on it;

[0054] Step 3: Perform post-processing according to the simulation results to analyze the aerodynamic performance of the aircraft.

[0055] Further, the creation of the three-dimensional mode...

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Abstract

The invention relates to a pneumatic simulation analysis method for a flapping-paddling-twisting flapping-wing air vehicle. The method is characterized by comprising the following steps: 1, establishing a three-dimensional model of an aircraft wing, and determining a flow field computational domain by combining an aerodynamic theory and a related empirical formula; 2, importing the wing and computational domain three-dimensional model into Ansys software, and performing mesh generation and fluid analysis on the wing and computational domain three-dimensional model; 3, performing post-processing according to a simulation result, and analyzing the aerodynamic performance of the aircraft. The method is easy to operate, high in calculation speed and high in accuracy, a good effect can be achieved on aerodynamic performance simulation analysis of the ornithopter, a visual solution can be provided in the optimization process of design of the ornithopter structure, and the problem solving efficiency is improved.

Description

technical field [0001] The invention belongs to the field of flapping-wing aircraft, and relates to the application of computational fluid dynamics in the flapping-wing aircraft, in particular to an aerodynamic simulation analysis method of a "flutter-stroke-twisting" flapping-wing aircraft. Background technique [0002] The flapping wing is an important structure of a new type of aircraft designed and manufactured based on the principle of bionics. The flapping wing flight method includes the advantages of fast take-off acceleration of fixed-wing flight and vertical lift and hovering of rotor flight, and can use very little energy. Long-distance flight is currently considered the most effective and flexible way of flying. The study of aerodynamic characteristics plays a key role in the design and research process of flapping-wing aircraft. The aerodynamic mechanism of flapping-wing flight is much more complicated than that of traditional flying methods. Therefore, it is ne...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/28G06F30/15G06F30/23G06F113/08G06F119/14
CPCG06F30/28G06F30/15G06F30/23G06F2119/14G06F2113/08Y02T90/00
Inventor 胡艳娟茹伟伟刘强王占礼张邦成柳虹亮陈延伟李静尹晓静庞在祥高智
Owner CHANGCHUN UNIV OF TECH
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