一种抑制激波边界层干扰强度的流动控制装置
By installing a curvature profile passive control unit array on the surface of the aircraft, airflow control is improved by utilizing curvature transition and stepped wake, thus solving the problem of shock wave/turbulent boundary layer interference. This achieves efficient suppression of shock wave/turbulent boundary layer interference, reducing peak heat flux and drag.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHINA ACAD OF AEROSPACE AERODYNAMICS
- Filing Date
- 2023-02-15
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies struggle to effectively control shock wave/turbulent boundary layer interference in supersonic and hypersonic vehicles, leading to high-frequency pulsations in aerodynamic drag, surface heat flux, and pressure loads, which in turn affect vehicle control and structural fatigue.
A control array consisting of multiple passive control units with curvature profiles is installed on the surface of the aircraft. The leading edge of the unit is tangent to the surface, and the trailing edge is higher than the surface to form a step. The airflow control is improved through curvature transition and step wake, and the intensity of shock wave/turbulent boundary layer interference is reduced.
It effectively reduces the high heat flux peak caused by shock wave/turbulent boundary layer interference, reduces the additional drag on the structure, reduces the size and weight of the device, has little impact on the structural flow capacity, and requires no additional energy input.
Smart Images
Figure CN116142455B_ABST