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Rocket plume simulation method

A simulation method, rocket plume technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as low calculation efficiency and poor reliability, achieve reliable flow field data, improve accuracy and reliability, The effect of improving computational efficiency

Active Publication Date: 2014-09-17
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the traditional modeling and simulation method, which assumes that the rocket nozzle outlet parameters are known, directly calculates the parameters of the plume flow field, has low calculation efficiency and poor reliability.

Method used

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Embodiment Construction

[0023] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings, but it is not limited thereto. Any modification or equivalent replacement of the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention should be covered by the present invention. within the scope of protection.

[0024] The invention provides a rocket plume simulation method, which specifically includes the following contents:

[0025] 1. General description of rocket plume flow field simulation method

[0026] The research idea is to first use Gambit software to generate the unstructured grid used for calculation and simulation, and define the boundary conditions to realize the simulation of Fluent. Fluent computational fluid software is used to simulate the plume flow field, and the velocity field, temperature field, and pressure field of the rocket plume flo...

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Abstract

The invention discloses a rocket plume simulation method which includes the following steps that an unstructured grid is generated by means of Gambit software and a boundary condition is set; the grid is led into Fluent, and plume flow field physical models are solved by means of Fluent software, wherein the plume flow field physical models include a turbulence model, a dispersed phase model and a combustion model; a boundary condition and an iteration initial value are set in the Fluent according to model requirements or actual situations, and flow field data are obtained through analog simulation. a parameter model for plume flow field compute is built based on the mechanism study of a rocket plume flow field and according to the combustion theory, hydromechanics and gas dynamics and with the consideration of combustion chemical reactions in a combustion chamber, main features of the plume flow field can be objectively described, flow field data on specific conditions are quickly obtained through simulation, input parameters are provided for compute of infrared features of rocket plumes, plume computer precision is improved, and plume simulation time is saved.

Description

technical field [0001] The invention belongs to the technical field of target characteristics and identification, and relates to a rocket plume simulation model. Background technique [0002] The calculation of the rocket plume flow field provides basic data for the calculation of the infrared radiation field of the plume. The calculation of plume flow field mainly includes the calculation of velocity field, temperature field and pressure field. There are various research methods for wake problems, which can be roughly divided into the following three types: semi-empirical and analytical methods, experimental measurement methods, and numerical simulation methods. Semi-empirical and analytical methods are mainly applied to relatively simple geometric models. When the physical process is not too complicated and the flow can be regarded as linear, the semi-empirical and semi-theoretical formula or analytical solution obtained after simplification is used to study the problem o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 秦兰琦张旺汪洪源王玉雷汪东生刘振奇张爱红范志刚
Owner HARBIN INST OF TECH
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