Hypersonic air inlet layout for annular combustion chamber

Abstract

The invention discloses a hypersonic air inlet layout for an annular combustion chamber. The hypersonic air inlet layout comprises the steps that the diameter, the length and the cone-to-column ratio of an aircraft are determined, and an aircraft profile is generated; a reference flow field is generated after the capture sectional area of an air inlet channel is determined, and streamline tracking is performed to generate an initial air inlet channel configuration; the initial air inlet channel configuration is cut off at the throat position, and an air inlet channel configuration is obtained; a double-air-inlet-channel configuration is generated based on the air inlet channel configuration, and a variable-section isolation section is generated by adopting a streamline tracking method to obtain the configuration of air inlet assemblies; and a bottom resistance surface of a steering engine bulge corresponding to each air inlet assembly is determined, an air inlet channel outer rectification profile is generated by using the air inlet channel front edge profile and the bottom resistance surface, and a steering engine and a control surface are installed on the inlet channel outer rectification profile. The lengths of the air inlet channel and the isolation section can be greatly reduced, so that the viscosity loss of flowing of an inner flow channel is reduced, the boundary layer is swept through shock waves, and the air inlet channel and the isolation section are uniform in flow field, high in flow field quality and high in back pressure resistance.

Description

technical field [0001] The invention relates to the technical field of intake port design, in particular to a hypersonic intake layout for an annular combustion chamber. Background technique [0002] Air-breathing hypersonic vehicle has huge military and civil potential because of its fast speed, long range and strong maneuverability. [0003] The air-breathing hypersonic vehicle faces the challenge of matching thrust and drag due to its fast flight speed and large flight resistance. Therefore, it is necessary to carry out the integrated design of the air inlet and the fuselage. The existing air-breathing hypersonic vehicle fuselage and air inlet integrated design are mainly divided into axisymmetric layout, lift body layout and waverider layout, which mainly use axisymmetric compression, two-dimensional compression intake and three-dimensional internal compression respectively. Switch to compressed intake form. [0004] The annular combustion chamber is mainly used in air...

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Problems solved by technology

[0008] Head air intake solution: The length of the engine internal flow channel of the head air intake solution is coupled with the length of the aircraft. The length of the engine internal flow channel needs to match the length of the aircraft, resulting in an excessively long internal flow channel and a large flow loss, thereby reducing engine performance or causing The engine cannot properly organize combustion;

[0009] Four-module X-type air intake scheme (two-dimensional air intake): This scheme can place the air intake on the body or tail of the aircraft, but because the boundary layer is thick, it must be designed with a partition that strips the boundary layer, resulting in structural weight Increased, increasing the difficulty of thermal protection

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