Variable overflow groove adjusting mechanism, scramjet engine and hypersonic aerocraft

Abstract

The invention discloses a variable overflow groove adjusting mechanism, a scramjet engine and a hypersonic aerocraft, and is suitable for a wide-speed-range aerocraft air inlet channel. The variable overflow groove adjusting mechanism comprises an adjusting plate and an adjusting mechanism body, wherein the adjusting plate is provided with an adjusting plate bottom; multiple adjusting plugs are arranged at the adjusting plate bottom and are inserted into an overflow groove of the scramjet engine; and the adjusting mechanism body is connected with the adjusting plate and used for driving the adjusting plate to move relative to the overflow groove so as to change the size of an opening of the overflow groove. Compared with a mode of adopting a front body / upper air inlet channel surface variable structure and a traditional mode of adopting the overflow groove with a fixed opening size, the starting Mach number can be effectively reduced, the quality of airflow entering a combustion chamber can be adjusted, and the structure is large in adjusting range, simple in structure, small in mass, high in engineering application realizability and convenient to implement.

Description

technical field [0001] The invention relates to the technical field of aircraft intake design, in particular to a variable overflow tank adjustment mechanism, a scramjet engine and a hypersonic aircraft. Background technique [0002] The main types of hypersonic vehicles include reusable vehicles and hypersonic missiles. At present, because hypersonic vehicles cannot take off directly from the ground only relying on scramjet engines, they must be combined with other power devices at low Mach numbers. Therefore, combined power such as rocket-based combined cycle or turbine-based combined cycle is often used. Or the turbine engine works, and after the aircraft is accelerated to a certain speed, the scramjet engine starts to work. The starting Mach number of the inlet not only affects the realization of combined power, but also determines the proportion of the auxiliary propulsion force in the entire propulsion system at a low Mach number, thus affecting the cost of hypersonic...

AI Technical Summary

Problems solved by technology

These two methods fix the starting Mach number of the inlet at a certain state, which cannot be adjusted independently according to different requirements, nor can the desorption of the overflow tank be performed according to different boundary layer thicknesses under different flight states. volume control

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