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A Design Method of Hypersonic Precursor Based on Two-zone Flow Field

A design method and hypersonic technology, which are applied to the combustion of the air intake of the power plant, ground installations, transportation and packaging, etc., can solve the problem of repeated adjustment and multiple iterations.

Active Publication Date: 2022-02-22
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The present invention provides a hypersonic precursor design method and device based on the two-zone flow field, which is used to overcome the defects in the prior art that the shape of the precursor and the inlet are designed separately, resulting in the need for repeated adjustments and multiple iterative calculations in the later stage. The integrated design realizes the precise control of the flow rate, which is beneficial to reduce the number of adjustments in the closed process of the design task and reduce the difficulty of the design

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  • A Design Method of Hypersonic Precursor Based on Two-zone Flow Field

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Embodiment 1

[0029] as attached Figure 1-3 As shown, the embodiment of the present invention provides a hypersonic precursor design method based on the two-zone flow field, including the following steps:

[0030] Step S1, according to the incoming flow conditions and the known direct shock wave profile line AB to obtain the direct shock wave dependent domain flow field flow direction tangential wall line AC;

[0031] According to the incoming flow conditions and the known direct shock wave profile, the characteristic line method and the space step method are used to solve the flow field in the direct shock wave dependent domain:

[0032] refer to figure 1 , where point A is the cone point of the aircraft precursor, and is also the starting point of the given shock AB, point B is the end point of the straight shock AB, and the line AB is the straight shock at a given shock angle. Take this as a design condition. Existing methods can be used for the characteristic line method and the spa...

Embodiment 2

[0137] Based on the first embodiment above, the embodiment of the present invention also provides a hypersonic precursor design device based on a two-zone flow field, including a memory and a processor, and the memory stores a hypersonic precursor design program based on a two-zone flow field , when the processor runs the hypersonic precursor design program based on the two-zone flow field, execute the steps of the method in any one of the above-mentioned embodiments.

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Abstract

The invention discloses a hypersonic precursor design method and device based on a two-zone flow field. The method includes: solving the direct shock wave dependent domain flow field from the incoming flow condition and the direct shock wave profile; using the flow capture requirements and the incoming flow condition Determine the starting point of the streamline; obtain the flow field in the expansion domain according to the outlet shape line of the dependent domain and the given expansion wave control factor, and trace the streamline in the two-area flow field from the streamline starting point to track the distance between the streamline and the known lip The distance is the target to optimize the control factor of the expansion wave, and stop the iteration when the set target is reached; the wall line of the flow field in the expansion domain is obtained by optimizing the control factor of the expansion wave; the generated wall line is used as the generatrix, and the horizontal axis passing through the starting point of the direct shock wave Rotate the axis of rotation according to a given center angle to obtain the profile of the front body of the intake port. Solve the problems in the prior art that the separate design of the precursor and the inlet makes the flow capture design complicated when repeated adjustments in the later stage, and provide an integrated design method to achieve precise control of flow capture and reduce design complexity.

Description

technical field [0001] The invention relates to the technical field of axisymmetric hypersonic aircraft, in particular to a design method for a hypersonic precursor based on a two-zone flow field. Background technique [0002] The function of the inlet port of an axisymmetric hypersonic vehicle is to capture a certain amount of airflow, decelerate and pressurize it, and then deliver the airflow to the combustion chamber for combustion. Due to the high velocity of the incoming flow, the hypersonic precursor needs to undertake part of the compression of the gas flow. At the same time, due to the needs of equipment loading, the aircraft front body often requires a large space, so the air intake is often arranged on the abdomen in the overall layout of the aircraft. Under this air intake system scheme, due to the long precursor, problems such as intake port flow control, boundary layer problems, and intake port start-up are brought about, and the design difficulty is significan...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64D33/02
CPCB64F5/00B64D33/02
Inventor 赵星宇徐尚成王翼范晓樯苏丹周芸帆闫郭伟
Owner NAT UNIV OF DEFENSE TECH