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Numerical Simulation of Flow Field and Convection/Radiation Coupling Heat Transfer in Multi-Nozzle Rocket

A radiation coupling and simulation method technology, applied in design optimization/simulation, instrumentation, geometric CAD, etc., can solve problems such as multi-nozzle rocket jet interference and difficulty in calculation, and achieve high vortex calculation accuracy and reduce calculation time.

Active Publication Date: 2019-02-19
NANJING UNIV OF SCI & TECH
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Problems solved by technology

[0004] The purpose of the present invention is to provide a simulation method of multi-nozzle rocket flow field and convection / radiation coupled heat transfer, to solve the problem that the mutual interference of multi-nozzle rocket jets is difficult to calculate

Method used

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  • Numerical Simulation of Flow Field and Convection/Radiation Coupling Heat Transfer in Multi-Nozzle Rocket
  • Numerical Simulation of Flow Field and Convection/Radiation Coupling Heat Transfer in Multi-Nozzle Rocket
  • Numerical Simulation of Flow Field and Convection/Radiation Coupling Heat Transfer in Multi-Nozzle Rocket

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Embodiment

[0108] A kind of simulation method about multi-nozzle rocket flow field and convection / radiation coupled heat transfer, according to the steps in the above-mentioned specific implementation mode, comprises the following steps:

[0109] Step 1, establishing a three-dimensional model of the multi-nozzle rocket;

[0110] combine figure 2 , the three-dimensional model includes a core stage 1, four boosters 2, and twenty nozzles 3, and is modeled in a 1:1 ratio with the actual engineering multi-nozzle rocket.

[0111] Step 2, using the multi-block structured grid method to divide the three-dimensional model into a grid;

[0112] combine image 3 , multi-block structured grid processing is performed on the geometric model, and a four-boost twenty-nozzle rocket is divided into grids. The final total number of grids is about 12.21 million.

[0113] Step 3. Establish the mathematical model of multi-nozzle rocket plume flow field and convective heat transfer: discretize the N-S mult...

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Abstract

The invention provides a simulation method for the flow field and convection / radiation coupling heat transfer of a multi-nozzle rocket. Firstly, a three-dimensional model of the multi-nozzle rocket isestablished. Secondly, the multi-block structured mesh method is used to mesh the three-dimensional model. The mathematical model of plume field and convection heat transfer of multi-nozzle rocket isestablished again. S multicomponent equation is discretized and integrated by AUSM + scheme. The inviscid flux at the boundary of the model is obtained by differentiation. Then the improved radiationmodel DOM is opened to obtain the radiation absorption coefficient of the model: the integral of radiation heat transfer by DOM model. Differential fundamental equation discretization; The radiationintensity values of each point are obtained; Finally, use RNG k-Epsilon turbulence model, output Mach number, temperature, pressure flow field and convection / coupled heat flux cloud map; The method ofthe invention can not only improve the calculation accuracy but also reduce the calculation cost, and the calculation result can provide guiding significance for the thermal protection of the bottomof the rocket.

Description

technical field [0001] The invention belongs to the field of numerical simulation of supersonic aircraft, in particular to a simulation method for multi-nozzle rocket flow field and convection / radiation coupled heat transfer. Background technique [0002] When the rocket engine is working, the propellant combustion products are ejected through the engine nozzle to form a high-temperature and high-speed gas jet, which will interfere with the launch tube wall and the rocket body, thereby affecting the stability and safety of the rocket launch system. At present, my country's next-generation high-thrust will use bundled launch vehicles with multiple nozzles. When the core stage engine and booster engine of the bundled launch vehicle work at the same time, the jets of multiple engines cross each other, and there is interference from external turbulence, forming a complex flow field in the bottom area of ​​the rocket, which intensifies the impact on the bottom area of ​​the rocke...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F2119/08G06F30/20Y02T90/00
Inventor 周志坛乐贵高
Owner NANJING UNIV OF SCI & TECH
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