A hypersonic velocity air-breathing type ramjet pneumatic thrust analysis method

A ramjet and hypersonic technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as the lack of integrated analysis methods

Active Publication Date: 2017-02-15
BEIJING MECHANICAL EQUIP INST
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  • Abstract
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  • Application Information

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Problems solved by technology

[0008] In view of the above analysis, the present invention aims to provide an analysis method for the aerodynamic thrus...

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  • A hypersonic velocity air-breathing type ramjet pneumatic thrust analysis method
  • A hypersonic velocity air-breathing type ramjet pneumatic thrust analysis method
  • A hypersonic velocity air-breathing type ramjet pneumatic thrust analysis method

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Embodiment Construction

[0043] Preferred embodiments of the present invention will be specifically described below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the application and are used together with the embodiments of the present invention to explain the principles of the present invention.

[0044] Acronyms and key term definitions

[0045] 1. Hypersonic

[0046] 2. Scramjet Combustors

[0047] 3. Analytical Solution

[0048] The specific embodiment of the present invention discloses an integrated analysis method for the aerodynamic thrust of a hypersonic air-breathing ramjet, such as figure 1 shown, including the following steps:

[0049] Step S1, acquiring parameters of the hypersonic air-breathing ramjet to be analyzed.

[0050] The two-dimensional structure of hypersonic air-breathing ramjet engine is as follows: figure 2 As shown, the engine internal flow path is divided into three parts: the intake port, the combustion chamber ...

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Abstract

The invention relates to a hypersonic velocity air-breathing type ramjet pneumatic thrust integrated analysis method. The method comprises the steps of: S1, acquiring the parameters of a to-be-analyzed hypersonic velocity air-breathing type ramjet; S2, calculating the mass flow rate of incoming flow air and the Mach number of an outlet of an admission passage according to the input parameters; S3, calculating the Mach number of an outlet of a combustor heat release section according to the Mach number of the outlet of the admission passage obtained through calculation in S2; S4, calculating the Mach number of an outlet of an exhauster of gas flow according to the Mach number of the outlet of the heat release section obtained through calculation in S3; S5, calculating ramjet thrust data according to the Mach number of the outlet of the exhauster obtained through calculation in S4. The method can perform hypersonic velocity air-breathing type ramjet pneumatic thrust calculation rapidly, provide a powerful tool for the pneumatic layout design optimization of hypersonic aerocrafts, provide optimal analysis results, and save the development time cost and the money cost for numerical simulation and experiment verification in the development of hypersonic aerocrafts.

Description

technical field [0001] The invention relates to the technical field of fluid mechanics, in particular to an analysis method for the aerodynamic thrust of a hypersonic air-breathing ramjet. Background technique [0002] At present, the research on hypersonic vehicles is a relatively cutting-edge and popular topic, among which the research on hypersonic air-breathing ramjet, the power core of hypersonic vehicles, is the top priority. [0003] The hypersonic air-breathing ramjet can be divided into three major components: the intake port, the combustion chamber (including the isolation section, the combustion section, and the expansion section), and the tail nozzle. The current theoretical research methods only analyze the specific components. , lacking an integrated analysis method covering the whole situation. E.g: [0004] Based on the Quasi-One-Dimensional High-Speed ​​Engine Model with Finite-Rate Chemistry of the finite chemical reaction, the governing equations of the ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/20Y02T90/00
Inventor 吴晨曦樊菁
Owner BEIJING MECHANICAL EQUIP INST
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