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Radiation equilibrium temperature calculation method considering slip correction

A technology of radiation balance and calculation method, applied in the directions of calculation, computer-aided design, design optimization/simulation, etc., can solve the problems of calculation failure, violent fluctuation of wall heat flow, and sliding temperature fluctuation, and achieve the effect of avoiding error iterative feedback amplification

Active Publication Date: 2021-07-02
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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AI Technical Summary

Problems solved by technology

At this time, in the process of solving the energy radiation balance equation of the wall temperature boundary processing, if there is a non-physical fluctuation in the wall temperature due to some reasons (such as numerical errors, etc.), this fluctuation will be transmitted to the gas slip through the slip relationship temperature, so that the slip temperature fluctuates; and because "the temperature of the micro-elements in the second layer of the wall is a definite value and the normal distance of the first layer of the wall is extremely small", this will lead to severe fluctuations in the heat flow of the wall; and the severe fluctuation of the heat flow The fluctuations in turn affect the solution of the energy radiation balance equation, so that the non-physical fluctuations are rapidly fed back and amplified, and even lead to calculation failure and divergence.

Method used

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  • Radiation equilibrium temperature calculation method considering slip correction
  • Radiation equilibrium temperature calculation method considering slip correction
  • Radiation equilibrium temperature calculation method considering slip correction

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Embodiment 1

[0083] Example 1: Numerical simulation of the non-equilibrium rarefied slip flow and surface radiation equilibrium coupling of the reflector. Returner looks like figure 2 As shown, the calculation and simulation state is a flight altitude of 85km and an incoming flow velocity of 7600.0m / s. The high-temperature gas model is a 5-component air chemical reaction Park model and a single temperature model, and the slip model is a classic Maxwell slip model; the aircraft surface is completely catalyzed (FCW) and completely non-catalyzed (NCW).

[0084] image 3 The calculation result and literature (Votta R, Schettino A, Ranuzzi G, Borrelli S, Hypersonic low-density aerothermo-dynamics of orion-like exploration vehicle[J].Journal of Spacecraft and Rockets, 2009) of the present invention are given. , 4(46):781~787). It can be seen that the heat flow results are closer to the DSMC results.

[0085] Figure 4 The distribution of wall surface radiation equilibrium temperature and w...

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Abstract

The invention discloses a radiation equilibrium temperature calculation method considering slip correction, which is mainly used for a coupling processing process of a slip temperature boundary and a wall radiation equilibrium temperature boundary in a process of numerical simulation of hypersonic velocity slip flow based on a Navier-Stokes control equation set. According to the method, on the basis of a traditional radiation balance energy equation, wall surface gas rarefaction slip temperature correction is introduced, a radiation balance equation based on slip temperature is formed, the slip temperature radiation balance equation is solved through implicit iteration to obtain gas slip temperature, and wall surface radiation balance temperature distribution is obtained through a surface temperature slip relation. The method is well compatible with two physical mechanisms of surface radiation energy balance and surface temperature rarefied slip effect, and is good in calculation stability and rapid in convergence.

Description

technical field [0001] The invention relates to the field of numerical simulation calculations, in particular to a calculation method for the radiation equilibrium temperature of a hypersonic thin slip flow wall surface. Background technique [0002] Wall radiation equilibrium temperature condition and surface gas temperature slip condition are two commonly used temperature boundary conditions in hypersonic flow simulation. For these two boundary conditions, separate studies are more common: when using the wall radiation equilibrium temperature condition, the rarefied slip effect of the surface gas is often ignored, that is, the surface gas temperature is considered to be the same as the wall temperature; and when considering the surface gas temperature glide When there is no effect, the isothermal wall condition is generally adopted, that is, the wall temperature is a certain fixed temperature condition. The combined use of the two is relatively rare. [0003] With the in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20G06F111/10G06F119/08
CPCG06F30/15G06F30/20G06F2111/10G06F2119/08Y02T90/00
Inventor 丁明松江涛陈坚强刘庆宗董维中高铁锁傅杨奥骁李鹏郭勇颜
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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