High-performance rectangular dual-channel external parallel-connection TBCC air inlet way and design method

Abstract

The invention discloses a high-performance rectangular double-channel outer parallel TBCC inlet. In terms of design, on the basis of the traditional two-stage external compression hypersonic inlet, the present invention designs the two-stage compression surface as a rotating lip cover, and adds a low-speed channel on this basis to realize the external parallel structure, and the low-speed The lower wall of the channel is designed as a variable structure, so that the shrinkage ratio in the low-speed channel can be adjusted, thereby improving the problem of poor starting performance in the low-speed channel. The two-stage compression surface of the high-speed channel and the lip cover of the low-speed channel are combined into one, and act as a mode conversion valve, which simplifies the structure of the intake port and enhances reliability. At the same time, the present invention also provides a specific embodiment of the rotating lip cover. The rotating lip cover is controlled by a servo motor in the form of a sliding thin plate introduced into the side wall of the passage, so that the movement of the rotating lip cover can be controlled. While satisfying the mode conversion, The flow control of the low-speed channel can also be realized by cooperating with the variable throat.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a high-performance rectangular dual-channel outer parallel TBCC inlet. Background technique [0002] With the advent of supersonic / hypersonic strike weapons, hypersonic vehicle technology has become the focus of research in various countries. The core technology of a hypersonic vehicle is the engine, that is, the high-performance propulsion technology. For the wide Mach number operating range required by hypersonic vehicles, it is difficult for general forms of aero-engines to meet the requirements, so combined engines emerged as the times require. Among them, the turbine-base-combine-cycle (Turbine-Base-Combine-Cycle) engine combines the aviation turbine with the aviation turbine, sub-combustion / scramjet engine to realize variable cycle work, so that the engine can work well under different working conditions Characteristics have become the focus of combined dynamics research at...

AI Technical Summary

Problems solved by technology

It can widen the working Mach number range of the intake port and solve the problem of poor starting performance of the low-speed channel

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