A method for designing a subsonic front-slat deflection law of an aircraft with buffet suppression

By discretizing the Mach number design points in the subsonic range and obtaining the flutter intensity through wind tunnel testing, the leading flap deflection law is constructed to move away from the flutter point, thus solving the subsonic flutter problem of high-performance aircraft, reducing flight test risks, and improving design accuracy.

CN117227997BActive Publication Date: 2026-06-12SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
Filing Date
2023-10-08
Publication Date
2026-06-12

AI Technical Summary

⚠Technical Problem

Modern high-performance aircraft are prone to chattering at subsonic speeds and medium angles of attack, which can lead to pilot frustration, aircraft structural fatigue, and unauthorized lateral movement. Existing design methods need to be explored and resolved during flight testing, which is costly and inefficient.

⚗Method used

Within a set subsonic Mach number range, discrete Mach number design points are established. Boom intensity is obtained through wind tunnel testing. A front flap deflection law is constructed to move away from the boom point. The front flap deflection law is designed in combination with aerodynamic characteristics.

🎯Benefits of technology

It effectively avoids flutter and unauthorized lateral movements during aircraft test flights, reduces test flight risks, and improves the predictive accuracy and safety of aircraft design.

✦ Generated by Eureka AI based on patent content.

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Abstract

The application belongs to the technical field of aircraft aerodynamic design, and particularly relates to a method for designing a front-slat deflection law of an aircraft for suppressing buffet. The method comprises the following steps: S1, discretely obtaining a plurality of Mach number design points in a set Mach number interval; S2, for each Mach number design point, controlling an aircraft model to reach a specified angle of attack attitude in a wind tunnel flow field in a specified angle of attack variation range according to a set step length; S3, based on a subsonic buffet characteristics wind tunnel test, obtaining buffet intensities of the aircraft in each front-slat deflection state at each Mach number design point, and forming the buffet intensities in a two-dimensional coordinate system; and S4, constructing a curve of the front-slat deflection varying with the angle of attack away from each buffet point at each Mach number design point. The application can avoid the phenomena of buffet and non-command lateral and longitudinal motion of the aircraft in flight test to the greatest extent, and effectively reduces the risk of the aircraft flight test.
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