Bionic slat design method based on owl wings

A design method, bionic wing technology, applied in computing, special data processing applications, instruments, etc., can solve problems such as low efficiency and long design time, and achieve the effect of avoiding design procedures, simple design methods, and improving aerodynamic lift

Inactive Publication Date: 2016-07-13
JILIN UNIV
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  • Application Information

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Problems solved by technology

[0004] Aiming at the problems of long design time and low efficiency faced in the conceptual design of the leading edge slat of the aircraft, the present invention aims to propose a design meth...

Method used

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  • Bionic slat design method based on owl wings
  • Bionic slat design method based on owl wings
  • Bionic slat design method based on owl wings

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Embodiment Construction

[0034] Below, the present invention will be further introduced in conjunction with the accompanying drawings and examples.

[0035] figure 1 It is the three-dimensional scanning model of the biological model of the present invention. Since the owl is under anesthesia during the scanning process, the configuration of the wings does not conform to the flying state, and certain adjustments are required. At the same time, it can be seen from the figure that the surface of the model is very rough and the edges are discontinuous, which also needs to be properly processed. Specific steps are as follows

[0036] (1) Determine the flight attitude of the owl wing;

[0037] When the owl is flying, the small wing feathers are generally retracted, and only when the owl is gliding at a low speed before landing, the small wing feathers will be stretched out. This is because the lift at this time is very small, and the owl needs to increase the lift coefficient by extending the small wing...

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Abstract

The invention discloses a bionic slat design method based on owl wings and belongs to the field of air vehicle wing design. The bionic slat design method mainly includes the steps of extracting three-dimensional geometric structures of the owl wings; constructing bionic wing profiles; determining bionic slat profile curves; determining fixed wing front edge profile curves; determining starting points E of internal and external profile curves of bionic slats; determining starting points F of the fixed wing front edge profile curves; determining ending points C of the internal and external profile curves of the bionic slats; determining ending points H of the fixed wing front edge profile curves. The bionic slat design method based on the owl wings has the advantages that design efficiency is improved substantially, continuity of internal profiles of the slats and fixed wing configuration curved surfaces is guaranteed, design quality of the profiles and the curved surfaces of the slats is improved, and lift augmentation effect of the bionic slats is remarkable, so that the requirements of designing and analyzing on improvement in wing profile aerodynamic force in an air vehicle conceptual design stage can be met; limitations of a traditional design method are avoided, rapid assessment and modification on performance in a preliminary design scheme are achieved, and a design period is shortened.

Description

technical field [0001] The invention belongs to the design technology of aircraft wings, and relates to the improvement of the prior design method of the section curve of the leading edge slat of the aircraft. Background technique [0002] At low speeds, there is often a laminar boundary layer near the leading edge of the wing. Due to the large adverse pressure gradient on the surface, the separation of the boundary layer occurs, which seriously affects the performance of the airfoil. In order to improve the lift characteristics of the aircraft during take-off and landing, the leading edge of the wing is equipped with auxiliary equipment for improving lift, called slats. In the conceptual design of the aircraft leading edge slat, the design of the inner surface of the slat and the shape of the leading edge of the fixed wing are very critical. At present, the commonly used method is to first place multiple sections given by discrete points in the span direction, and then us...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 葛长江胡兴军叶辉杨瀚博曹杰汛李冠群
Owner JILIN UNIV
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