Two-dimensional supersonic air inlet passage with variable structure

Abstract

The invention discloses a two-dimensional supersonic air inlet passage with a variable structure. The air inlet passage and an aircraft body are of an integrated structure, a fixing plate is positioned in the air inlet passage and is arranged parallel to an upper supporting plate, a piston barrel and a piston rod are fixedly connected with an upper fixed support and a lower fixed support respectively, the piston barrel and the piston rod are synchronously matched and are positioned between the fixing plate and the upper supporting plate, a front compression plate is articulated with a movable compression plate by a first rotating rod, the movable compression plate is articulated with the upper supporting plate by a second rotating rod, the upper supporting plate and the air inlet passage are articulated by a third rotating rod, and two ends of each of the second rotating rod and the third rotating rod are positioned in a front sliding groove and a rear sliding groove on the two side walls inside the air inlet passage respectively for movement. The air inlet passage has simple structure and has strong realizability in engineering application, the compression angle of the air inlet passage is changed to directly adjust the quality of air flows entering into a combustion chamber, the aerodynamic performance and the working state of the air inlet passage operating in a wide range of mach number are ensured, and the working efficiency and the aerodynamic performance of the air inlet passage are greatly improved.

Description

technical field [0001] The invention relates to the technical field of rocket ramjet engines, in particular to a variable-structure two-dimensional supersonic inlet. Background technique [0002] For the inlet of a hypersonic air-breathing aircraft with a wide Mach number, that is, the working range of Ma3-Ma8, the excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range, and At the non-design point, whether it can start normally and provide the combustion chamber with an air flow that meets certain airflow quality requirements is an important factor to be considered in the design of the intake port. [0003] For the two-dimensional supersonic inlet, the compression angle of the compression surface is small at low Mach number, and the compression angle is large at high Mach number. The use of a fixed structure inlet will affect the performance of the inlet, and even Causes the intake to not start. [0...

AI Technical Summary

Problems solved by technology

[0004] Invention patent CN 103790710 A discloses "a rocket-based combined cycle engine variable-structure intake port" that can better realize the design of the variable-structure intake port, and can meet the startability requirements through step-by-step adjustment, so that the engine combustion chamber can work normally , but there are many parts in the mechanism, the mechanical structure is relatively complicated, the design of the mechanism is cumbersome, the processing is difficult, and it is not easy to realize in engineering; the invention patent CN 103939217 A relates to a "rectangular section hypersonic variable geometry inlet and its design method "and working mode" is to increase or decrease the Mach number flow capture rate of the intake port through the rotation of the adjustable side of the lip cover, but this method cannot change the size of the compression surface corresponding to the compression angle, which may easily lead to the flow entering the combustion chamber Unstable airflow, which affects engine performance

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