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Integrated Method of Nozzle Parameter Modeling and Flow Field Calculation

A flow field calculation and nozzle technology, which is applied in calculation, electrical digital data processing, special data processing applications, etc., can solve the problems of discontinuous flow field, large parameter input and labor costs, and inability to obtain data support, etc., to achieve Save time and manpower and improve accuracy

Active Publication Date: 2018-11-09
中国航天科工集团第六研究院二一〇所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage is that in the calculation process of the flow field parameters of the nozzle, only the flow field parameters of a limited number of sections in the continuous curve of the inner surface of the nozzle can be obtained. Improper selection of the calculation section will cause the flow field to be discontinuous, and sometimes effective data support cannot be obtained. With the subdivision of the calculation section, although the calculation result is more accurate, the calculation involves greater parameter input and labor costs

Method used

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  • Integrated Method of Nozzle Parameter Modeling and Flow Field Calculation
  • Integrated Method of Nozzle Parameter Modeling and Flow Field Calculation
  • Integrated Method of Nozzle Parameter Modeling and Flow Field Calculation

Examples

Experimental program
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Effect test

Embodiment 1

[0036] Total length of inner surface: 233; mm;

[0037] Throat radius: 24.36; mm;

[0038]Taking the nozzle inlet as the 0 point, the segmental interval along the nozzle axis X and the segmental function y=z(x) of the inner surface are respectively:

[0039] x=0mm~16mm; y=101-tan(15°) x, mm;

[0040] x=16.1mm~25.8mm; mm;

[0041] x=25.9mm~47.9mm; mm;

[0042] x=48.0mm~74.2mm; mm;

[0043] x=74.3mm~80.2mm; y=24.36, mm;

[0044] x=80.3mm~233mm; y=74+tan(18°)·(x-233), mm.

[0045] Δx is taken as 0.01mm.

Embodiment 2

[0047] Total length of inner surface: 422mm;

[0048] Throat radius: 22.5mm;

[0049] X segment range: 0~11.78, 11.80~19.99, 20.00~56.51, 56.52~88.66, 88.67~155.56, 155.57~170.93, 170.94~195.53, 195.54~202.53, 202.54~254.30, 254.31~422

[0050] Segmented functions: 10;

[0051] Δx is taken as 0.1 mm.

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Abstract

The invention provides a nozzle parameter modeling and flow field calculation integration method which adopts a case multi-branch selection structure. An internal surface segmented function model of the nozzle is built along the x direction, and the nozzle section subdivision is directly controlled by the section increment delta x, the section interval of the nozzle is controlled by step size control and calculation, so that the enough dense section parameter is obtained, and finally through the iterative computation, the section flow field data which is nearly continuous is obtained. The problem of flow field parameter incontinuity caused by the incontinuity of the intercepted section in the original nozzle internal flow field calculation is solved, the flow field parameter defect caused by man-made reasons is avoided, and the artificial cost is reduced.

Description

technical field [0001] The invention relates to segmented parametric modeling of the inner surface of a nozzle and integrated calculation of flow field parameters, which is suitable for the calculation of airflow parameters in the nozzle of a conventional solid rocket motor and provides data support for the structure and heat protection design of the nozzle. Background technique [0002] The theoretical calculation of the flow field parameters of the solid rocket motor nozzle is derived from the classic one-dimensional absolute energy isentropic flow, that is, the total temperature and total pressure of the gas remain unchanged during the flow process from the inlet of the convergent section to the outlet section of the divergent section. Starting from the continuity equation, the flow function and velocity coefficient of each section are calculated, and on this basis, other airflow parameters of each section are solved. [0003] The general theoretical calculation process i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/17
Inventor 王一林
Owner 中国航天科工集团第六研究院二一〇所