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Numerical method for predicting jet noise of single-nozzle carrier rocket

A technology for launch vehicles and numerical methods, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as sabotage, rocket launch failure, endangering rocket launch safety, etc., and achieve low diffusion, good numerical accuracy, and reduced The effect of computing time

Active Publication Date: 2019-11-15
NANJING UNIV OF SCI & TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The rocket jet noise may cause damage to the artificial satellites inside the fairing and other payloads and the control devices of the interstage section, endangering the launch safety of the rocket, and in severe cases, it will cause the launch failure of the rocket

Method used

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  • Numerical method for predicting jet noise of single-nozzle carrier rocket
  • Numerical method for predicting jet noise of single-nozzle carrier rocket
  • Numerical method for predicting jet noise of single-nozzle carrier rocket

Examples

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Embodiment

[0060] combine figure 1 , a numerical method for predicting single-nozzle rocket jet noise, according to the steps in the above-mentioned specific implementation mode, comprises the following steps:

[0061] Step 1. Establish a three-dimensional model of a single-nozzle rocket;

[0062] combine figure 2 , the three-dimensional model includes rocket 1, nozzle 2 and diversion tank 3, and is modeled in 1:1 ratio with the actual engineering multi-nozzle rocket.

[0063] Step 2, using the partition structured grid method to divide the three-dimensional model into a grid;

[0064] combine image 3 , the geometric model is processed with partitioned structured grid, and the single nozzle rocket with diversion groove is divided into grids. The final total number of grids is about 3.7 million.

[0065] Step 3. Establish the mathematical model of the single-nozzle rocket jet flow field: use the anisotropic two-equation Cubic k-ε turbulence model to calculate the steady-state flow f...

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Abstract

The invention discloses a numerical method for predicting jet noise of a single-nozzle carrier rocket. The numerical method comprises the steps: firstly building a single-nozzle carrier rocket three-dimensional model, and carrying out the mesh generation of the single-nozzle carrier rocket three-dimensional model through a partitioning structured mesh method; thirdly, calculating a gas jet steady-state flow field of the single-nozzle carrier rocket to obtain initial sound field information; obtaining initial sound field information from the steady-state flow field, and reconstructing a turbulence pulsation signal by adopting a nonlinear disturbance equation; and finally, based on an FW-H equation of an acoustic comparison method, collecting noise information of a far-field receiving point,and outputting a frequency spectrum curve of the noise receiving point. According to the numerical method, the grid number is reduced and the calculation efficiency is improved while the calculationprecision is ensured.

Description

technical field [0001] The invention belongs to the interdisciplinary field of fluid mechanics and acoustics, and in particular relates to a numerical method for predicting jet noise of a single-nozzle carrier rocket. Background technique [0002] Space launch vehicle is generally composed of power plant, rocket body structure and control system and other components. The structure is generally composed of the head, head fairing, oxidant storage tank and fuel (combustion agent) storage tank, instrument cabin, interstage section, engine thrust structure, tail tank and other parts, and the parts that need to be separated are provided with separation and connection devices. Among them, the fairing is used to protect the satellite and other payloads to prevent the satellite from being affected by harmful environments such as aerodynamic force, aerodynamic heating, and acoustic vibration. It is an important part of the launch vehicle. When the rocket is launched into space, the l...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 邢成龙乐贵高
Owner NANJING UNIV OF SCI & TECH
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