一种基于吹吸气的混合层流与激波抖振复合控制方法

By setting porous skin and channels on the leading edge of the wing and using a high-pressure air source to switch between intake and exhaust modes, the problem of increased flutter intensity caused by mixed laminar flow control was solved, achieving a balance between lift increase, drag reduction, and flight safety.

CN122402771APending Publication Date: 2026-07-17INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
Filing Date
2026-06-18
Publication Date
2026-07-17

AI Technical Summary

Technical Problem

Existing hybrid laminar flow control methods, while increasing lift and reducing drag, also lead to increased flutter intensity and reduced flight safety.

Method used

A hybrid laminar flow and shock wave flutter control method based on blowing and sucking is adopted. A porous skin and channels are set on the leading edge of the wing by an ejector vacuum generator. The high-pressure air source is used to switch between the sucking and blowing modes to achieve laminar flow control and flutter stability adjustment.

Benefits of technology

While achieving increased lift and reduced drag, it effectively reduces the intensity of flutter, improves flight safety, and ensures the stability and safety of the aircraft.

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Abstract

本发明公开了一种基于吹吸气的混合层流与激波抖振复合控制方法，属于航空飞行器主动流动控制或调节领域，目的在于解决现有混合层流控制方法，在实现增升减阻技术效果的前提下，由于层流控制的作用，致使边界层抗分离能力大幅度减弱，导致抖振强度增加的问题。该方法包括如下步骤：S1、吸气模式：在引射式真空发生器的负压作用下，机翼前缘的气流依次经多孔蒙皮、蒙皮支撑件上的气体通孔、槽道、第一气体管道、第一吸气口进入引射式真空发生器中；进入引射式真空发生器内的气体依次经第三排气口、第三气体管道排出；S2、吹气模式：引射式真空发生器内的气体依次经第一吸气口、第一气体管道、槽道、蒙皮支撑件上的气体通孔、多孔蒙皮排出。
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