A Symmetrical Variable Structure Supersonic Inlet Regulator

Abstract

The invention discloses a regulation device with a symmetric type variable structure for a supersonic inlet. The regulation device comprises a front body compression plate, a throat upper panel, a combustion chamber upper panel, regulation devices and sliding mechanisms, wherein the front body compression plate and the combustion chamber upper panel are connected with the throat upper panel through the sliding mechanisms and the regulation devices; the regulation devices are symmetrically fixed to the throat upper panel; and a plurality of sliding mechanisms are symmetrically installed on the front body compression plate and the combustion chamber upper panel respectively. According to the regulation device, through the regulation devices, the size of a compression angle of an inlet duct and the height of a throat are changed, the quality and the air flow of an airflow which enters a combustion chamber, and the inlet duct is in a better working state; when the inlet duct works at a low Mach number, the compression angle of the front body compression plate is reduced, and meanwhile, the height of the throat is increased so as to change the starting performance of the inlet duct and improve the performance of an engine; and along with increase of the Mach number, the compression angle is increased, the height of the throat is also reduced, the internal contraction ratio is increased, the static pressure at the outlet of the inlet duct is strengthened, and the overall performance of an aircraft is improved.

Description

technical field [0001] The invention relates to a supersonic inlet, in particular to a symmetrical variable-structure 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, in order to ensure its normal operation, it is difficult to ensure that the inlet is under the entire flight envelope only by changing the lip or wedge. The excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range. At the non-design point, whether it can start normally and provide air with a certain quality requirement for the combustion chamber is a problem. One of the factors that need to be considered in the design of the air inlet, and the size of the air flow is also a factor that needs to be considered in the design. [0003] Invention patent CN 103790710 A discloses "a rocket-based com...

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Problems solved by technology

[0002] For the inlet of a hypersonic air-breathing aircraft operating in the wide range of Mach number Ma3-8, in order to ensure its normal operation, it is difficult to ensure that the inlet is under the entire flight envelope only by changing the lip or wedge. The excellent aerodynamic performance at the design point cannot guarantee that it can work normally and stably in the working range. At the non-design point, whether it can start normally and provide air with a certain quality requirement for the combustion chamber is a problem. One of the factors that need to be considered in the design of the air inlet, and the size of the air flow is also a factor that needs to be considered in the design

[0003] Invention patent CN 103790710 A discloses "a rocket-based combined cycle engine variable-structure inlet", the variable-structure inlet can better realize the design of the variable-structure inlet, and can meet the startability requirements through step-by-step adjustment. The combustion chamber of the engine works normally, but because the horizontal plate is used in the structure to act as the hydraulic cylinder to realize the movement of the horizontal plate, the air flow at the throat can be adjusted less; Geometric inlet and its design method and working method”, the variable geometric inlet and its design method and working method are to increase or decrease the flow of the inlet through the rotation of the adjustable side of the lip cover, but this method cannot be changed The size of the compression surface corresponds to the compression angle, which can easily lead to unstable airflow entering the combustion chamber, thereby affecting the performance of the engine; in the invention patent GB 2242402 A, "a variable-structure supersonic aircraft intake system" is disclosed, but In order to achieve the purpose of variable structure, the mechanical structure device used is more complicated, and it is more difficult to realize in engineering

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