A Variable Structure Two-Dimensional Supersonic Inlet Adjustment Mechanism

Abstract

The invention discloses a variable structure two-dimensional supersonic air intake regulating mechanism. The variable structure two-dimensional supersonic air intake regulating mechanism comprises a front body compression panel, a throat upper panel, a combustion chamber upper panel, connecting link mechanisms, a telescoping mechanism and hydraulic mechanisms, wherein the front body compression panel and the combustion chamber upper panel are connected with the throat upper panel through the telescoping mechanism; two groups of connecting link mechanisms are parallelly and symmetrically mounted on the surface of the throat upper panel; and two groups of hydraulic mechanisms are fixed to the side opposite to the two groups of connecting link mechanisms. The connecting link mechanisms and the telescoping mechanism move under the action of the hydraulic mechanisms, the movement of the telescoping mechanism changes the inclination angles of the front body compression panel and the combustion chamber upper panel, and at the same time, the throat upper panel moves horizontally from top to bottom, so that the stability of air flow entering a combustion chamber can be ensured. The incoming air is decelerated and pressurized in an air intake through the front body compression panel, the throat upper panel moves to change the throat altitude, so that the air intake can be guaranteed to start normally in a wide Mach number range and is in a good operating condition, and the operation efficiency and aerodynamic performance of the air intake are improved.

Description

technical field [0001] The invention relates to a supersonic inlet regulating mechanism, in particular to a variable-structure two-dimensional supersonic inlet regulating mechanism. Background technique [0002] For the inlet of a hypersonic air-breathing aircraft operating in the wide Mach number Ma3-8 range, the excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range, and it is in the non-design 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. For an air-breathing engine, the quality of the air entering the engine is a prerequisite for its work. If the airflow is relatively turbulent, the engine will not be able to work at its best, which will affect the overall performance of the aircraft. [0003] For the two-dimensional supersonic inlet, the compressi...

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Problems solved by technology

[0004] Invention patent CN 103790710 A proposes "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 103939217 A, a "rectangular cross-section hypersonic variable geometry inlet and its design method and "Working mode" 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 2242402 A, "an inlet system for a variable-structure supersonic aircraft" is proposed. In order to achieve the purpose of variable structure, the mechanical structure device adopted is relatively complicated, and it cannot guarantee the air flow quality

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