Design method of internal parallel hypersonic dual-channel inlet

Abstract

The invention provides a design method of an internal parallel type hypersonic-speed and double-channel air inlet channel and relates to a hypersonic-speed air inlet channel of an aircraft. The design method comprises the following steps: designing an external pressure section of the air inlet channel; designing an internal pressure section of a punching channel; designing an isolation section of the punching channel; designing a flow division scheme; designing a low-speed turbine channel with a working Mach number range of a Mach number Ma=0 to 1.8. The designed binary internal parallel type turbine-based combined circulating power air inlet channel structurally comprises the high-speed punching channel, the low-speed turbine channel and a flow division plate of the air inlet channel. The punching channel is composed of the external pressure section of the air inlet channel, the internal pressure section of the punching channel, the flow division plate and the isolation section of the punching channel; a mold surface is generated by adopting an isentropic method. The turbine channel is composed of the external pressure section of the air inlet channel, the internal pressure section of the punching channel, the flow division plate and an expansion section of the turbine channel, and a mold surface is generated through an isentropic compression law and an area uniform transition manner.

Description

technical field [0001] The invention relates to a hypersonic air intake of an aircraft, in particular to a design method of an internal parallel hypersonic dual-channel air intake. Background technique [0002] Since the advent of aircraft, people have been pursuing higher performance and faster speed, from the earlier subsonic flight, to transonic, supersonic, and now hypersonic flight ([1] Zhang Huajun, Guo Rongwei, Xie Lvrong. Design and Verification of Inner Parallel TBCC Inlet Scheme [J]. Aerodynamics Journal, 2012, 27(11): 2475-2483). People have higher and higher requirements for power devices. For a single-mode inlet, it is difficult to meet the flight Mach number range from subsonic to hypersonic required by hypersonic aircraft. For this reason, people began to carry out a series of research on the combined cycle engine, which contains two working modes, which can not only solve the starting problem at low Mach number, but also provide enough power for hypersonic f...

AI Technical Summary

Problems solved by technology

However, compared with other single-mode engines, the intake port of the TBCC engine has a more complex structure, more variable geometry parts, and the combination and conversion control between the two modes is particularly difficult. Therefore, from the 1960s to the present, There are not many studies on this type of intake port, so there is great research value on the conversion between ramming and turbine modes of TBCC engines

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