A variable structure two-dimensional supersonic air inlet adjusting device

Abstract

The invention discloses an adjusting device for a variable-structure two-dimensional supersonic inlet. The device comprises a front compressing plate, an upper panel of a throat, an upper panel of a combustion chamber, a linkage mechanism, a hydraulic mechanism and a bracket, wherein the front compressing plate and the upper panel of the combustion chamber are connected with the upper panel of the throat through hinges; a base is fixed to the upper panel of the throat; the bracket is positioned at the upper part of the upper panel of the throat; the linkage mechanism and the hydraulic mechanism are positioned in match at two ends of the bracket and are also in fit connection with the base and corresponding bracket fixing seats. The adjusting device for the variable-structure two-dimensional supersonic inlet is simple in structure, and high in construction practicability; a compressing angle can be directly changed to enable stable combustion of air flowing into the combustion chamber; the inlet can be normally started within a wide mach number range, and thus the inlet can work in a good state. The adjusting device is high in transferability and generality; the size of the device can be changed to fit any air-breathing vehicle equipped with the two-dimensional supersonic inlet. Therefore, the integral design of an air-breathing engine and an air-breathing vehicle body can be improved, and as a result, the overall performances of the air-breathing vehicle can be improved.

Description

technical field [0001] The invention relates to an inlet regulating device, in particular to a variable-structure two-dimensional supersonic inlet regulating device for wide Mach number operation. Background technique [0002] For the inlet of a hypersonic air-breathing aircraft operating in the wide range of Mach number Ma3-8, the excellent aerodynamic performance at the design point cannot guarantee its normal and stable operation in the working range, and it is not at the design point. Whether it can start normally at the point and provide the air with good quality requirements for the combustion chamber are all factors that need 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 ...

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Problems solved by technology

[0004] Invention patent CN 103790710A discloses "a rocket-based combined cycle engine variable-structure inlet", which can better realize the design of the variable-structure inlet, and through graded adjustment, it can meet the requirements of starting performance and normal operation of the engine combustion chamber , but there are many parts in the mechanism, the mechanism design is cumbersome, the mechanical structure is relatively complicated, the processing is difficult, and it is not easy to realize in engineering; in the invention patent CN 103939217A, "rectangular cross-section hypersonic variable geometry inlet and its design method and work "method" is to increase or decrease the flow 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 angle corresponding to the compression surface, which will easily lead to unstable airflow entering the combustion chamber, thereby affecting The performance of the engine; in the invention patent GB 2242402A, "an inlet system for a variable-structure supersonic aircraft" was proposed, but in order to achieve the purpose of variable structure, the mechanical structure device adopted by the inlet system is relatively complicated. It is more difficult to realize in

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