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Design method of three-dimensional inward turning air inlet channel capable of simultaneously controlling shock wave and pressure distribution

A pressure distribution and air inlet technology, applied in computing, image data processing, special data processing applications, etc., can solve the problem that the incident shock wave and the isentropic compression process cannot be controlled at the same time, and achieve the effect of widening the degree of freedom

Active Publication Date: 2020-08-18
NANCHANG HANGKONG UNIVERSITY
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Problems solved by technology

However, in the existing three-dimensional internal turning inlet design process, the two factors are usually considered separately, and it is impossible to realize the simultaneous controllability of the incident shock wave and the isentropic compression process.

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  • Design method of three-dimensional inward turning air inlet channel capable of simultaneously controlling shock wave and pressure distribution
  • Design method of three-dimensional inward turning air inlet channel capable of simultaneously controlling shock wave and pressure distribution
  • Design method of three-dimensional inward turning air inlet channel capable of simultaneously controlling shock wave and pressure distribution

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Embodiment Construction

[0029] The implementation of the present invention will be described in detail below with reference to the drawings and examples, so as to fully understand and implement the implementation process of how to use technical means to solve technical problems and achieve technical effects in the present invention.

[0030] The main implementation steps of the three-dimensional inward turning inlet design method with simultaneous controllable shock wave and pressure distribution include:

[0031] (1) Design the incoming flow conditions and the incident shock wave curve 1, and inversely calculate the wall profile according to the characteristic line method. The incoming flow condition is the design condition of the aircraft, and the incident shock wave curve 1 can be designed as a curved incident shock wave. Using the characteristic line method, the incoming flow condition and the incident shock wave curve 1 are used as input conditions to solve the right-hand characteristic line 2 re...

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Abstract

The invention relates to a three-dimensional inward turning air inlet channel design method capable of controlling shock wave and pressure distribution at the same time. The method comprises the following steps:(1) incoming flow conditions and incident shock wave curves are designed, and wall surface molded lines are reversely solved according to a characteristic line method; (2) extracting pressure distribution of the wall surface molded line obtained in the step (1), and designing downstream pressure distribution; (3) according to the pressure distribution obtained in the step (2), reverselysolving a wall surface molded line by utilizing a characteristic line method; (4) taking the three-dimensional revolution of the wall surface molded line obtained in the step (3) as a bus of a basicflow field, and solving the whole flow field; (5) designing a three-dimensional inward turning air inlet passage inlet in polar coordinates, and performing streamline tracking in the basic flow fieldobtained in the step (4) to obtain a three-dimensional inward turning air inlet passage compression profile; and (6) the three-dimensional inward-turning air inlet channel compression molded surface obtained in the step (5) is stretched in the equal-straight-direction backward direction to obtain an isolation section. The advantages of the three-dimensional inward turning air inlet channel are kept, meanwhile, the incident shock wave and wave back isentropic compression process is designed, and therefore a new degree of freedom is introduced for design of the three-dimensional inward turning air inlet channel.

Description

technical field [0001] The invention relates to the technical field of three-dimensional inward turning inlet design, in particular to a design method for a three-dimensional inward turning inlet with simultaneously controllable shock waves and pressure distribution. Background technique [0002] The research and development and trial production of hypersonic vehicles is one of the focuses of space technology research, and it is the technological commanding heights that all aviation powers are vying to occupy. To achieve hypersonic flight, the first technical problem to be solved is scramjet technology. The intake duct is located at the front end of the scramjet as a compressed air component, which will provide as much high-energy airflow as possible for the downstream. Therefore, scholars at home and abroad have proposed a series of design methods for the compression form of the inlet, mainly including: binary inlet, axisymmetric inlet, and side pressure inlet, and have ca...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06T17/00G06F30/15
CPCG06T17/00G06F30/15Y02T90/00
Inventor 李怡庆韩美东李光昱
Owner NANCHANG HANGKONG UNIVERSITY
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