Low External Resistance Hyper/Hypersonic Inlet and Shock/Boundary Layer Interference Control Method

Abstract

The invention provides a low-external-resistance supersonic / hypersonic speed inlet. A two-dimensional bump is arranged at an inlet of the supersonic / hypersonic speed inlet, and partial air discharge seam / hole arrays are arranged at the inward concave positions of the windward side and the leeward side; and meanwhile, an air discharge cavity below the bump is divided into two sub-cavities, and electromagnets and a metal plate with a folded corner are adopted for achieving control over opening and closing of the two air discharge sub-cavities. By means of control over opening and closing of the two air discharge sub-cavities, the low-external-resistance supersonic / hypersonic speed inlet can adapt to shock wave intensity and incidence point position changes brought by inlet working mach number and attitude angle changes, the optimal control ability on boundary layer separation caused by shock wave / boundary layer disturbance of a lip cover is obtained, and the remarkable effects of widening the working range of the low-external-resistance supersonic / hypersonic speed inlet and increasing the total pressure recovery coefficient are achieved. Due to the high flowing control ability of the low-external-resistance supersonic / hypersonic speed inlet, the inlet is allowed to adopt the design of the horizontal lip cover, and therefore the external pneumatic resistance of an aircraft can be effectively reduced.

Description

technical field [0001] The invention relates to the technical field of flow control of high-speed aircraft, in particular to a low external resistance supersonic and hypersonic inlet design. [0002] The present invention also provides a wide-area control method for the lip shock wave / boundary layer interference of the air inlet. Background technique [0003] The phenomenon of oblique shock / boundary layer interference widely exists in the inlet of supersonic and hypersonic aircraft, especially the lip shock / boundary layer interference at the mouth of the inlet, and the separation of the boundary layer air flow at the inlet is It is a prominent problem in the flow organization of the channel in the intake port. It not only leads to a significant loss of total pressure, but also greatly reduces the anti-backpressure capability of the intake port. In the starting state, the available working envelope of the intake port is reduced. This problem is especially obvious in superso...

AI Technical Summary

Problems solved by technology

However, although such conventional control methods can achieve certain control effects, there are also obvious deficiencies.

For example, the method of venting through slots realizes the control of flow separation by releasing a large amount of low-energy flow in the boundary layer, and at the same time brings problems such as large additional venting resistance, heavy thermal protection burden, and loss of captured flow; the installation of vortex generators The control ability of the control method is relatively weak, and the structure of the vortex generator itself is relatively fragile, and it is easily damaged under the impact of high-speed airflow. At the same time, there is ablation problem at a high Mach number; The pressure effect and acceleration effect can effectively control the boundary layer separation that occurs on the convex outer surface of the bulge, but when the shock wave / boundary layer interference occurs on the concave inner surface of the bulge, the control effect of the bulge is relatively limited

Images