A closed variable structure two-dimensional supersonic inlet

Abstract

The invention discloses a two-dimensional supersonic inlet of an enclosed variable structure. The two-dimensional supersonic inlet comprises a machine body, an inlet and a combustor upper panel actuating device, wherein the machine body and a fixed compression plate are of an integral structure; a sector plate is connected with the fixed compression plate through a rotating shaft, and rotates, adjoining the side wall of the machine body, in a sector groove; a movable compression plate moves in a groove and is connected with a combustor upper panel through a rotating shaft; and the combustor upper panel actuating device drives the combustor upper panel to move up and down along a front chute and a rear chute which are formed in the inside wall of the machine body in the vertical direction. By adoption of the two-dimensional supersonic inlet, under the condition of ensuring that the inlet is sealed, the quality of airflow entering a combustor can be directly adjusted through changing the size of a compression angle of the inlet. The two-dimensional supersonic inlet of the enclosed variable structure realizes steady transition from low-Mach-number operation to high-Mach-number operation to reduce the aerodynamic resistance, and can be started up within a wide Mach number range to be in a good working state, thereby being improved in working efficiency and aerodynamic performance.

Description

technical field [0001] The invention relates to a two-dimensional supersonic inlet, in particular to a closed variable-structure two-dimensional supersonic inlet for wide Mach number work. Background technique [0002] For the inlet of a hypersonic air-breathing aircraft whose Mach number Ma is in the range of 3 to 8, the excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range. Whether it can start normally at the design point and provide air with a certain quality requirement for the combustion chamber is an important factor to be considered in the design of the intake port. If the intake port cannot work at the design point Ma6.5 at Ma2.5, it may be If the compression angle is too large, the slope of the shock wave will become larger, the energy loss will be greater, and the air flow will be blocked, causing serious overflow, or the throat height will be too small to reduce the intake air volume, or t...

AI Technical Summary

Problems solved by technology

[0002] For the inlet of a hypersonic air-breathing aircraft whose Mach number Ma is in the range of 3 to 8, the excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range. Whether it can start normally at the design point and provide air with a certain quality requirement for the combustion chamber is an important factor to be considered in the design of the intake port. If the intake port cannot work at the design point Ma6.5 at Ma2.5, it may be If the compression angle is too large, the slope of the shock wave will become larger, the energy loss will be greater, and the air flow will be blocked, causing serious overflow, or the throat height will be too small to reduce the intake air volume, or the external contraction ratio will be too large , it may also cause the engine not to start, etc. At this time, the use of a fixed-geometry intake port will affect the performance of the intake port, and even cause the intake port to fail to start.

[0003] Invention patent CN 103790710A discloses "a rocket-based combined-cycle engine variable-structure inlet", the rocket-based combined-cycle engine variable-structure inlet can better realize the design of the variable-structure inlet. Meet the requirements of startability and make the combustion chamber of the engine work normally; however, there are many mechanical parts, the mechanical structure is more complicated, the mechanism design is more cumbersome, the processing is more difficult, and it is not easy to realize in engineering

[0004] In the invention patent CN 103939217A, a "rectangular cross-section hypersonic variable geometry inlet and its design method and working method" is proposed. The design method and working method are to increase or decrease the intake air by rotating the adjustable side of the lip cover. However, this design method and working 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

[0005] In the invention patent GB 2242402A, "an air intake system for a variable-structure supersonic aircraft" is disclosed, but this system cannot guarantee the quality and sealing of the airflow entering the air intake

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