Thermochemical unbalanced multistage gas model adaptive algorithm

A non-equilibrium, thermochemical technology, applied in the field of aerodynamics, which can solve the problems of rigidity, non-convergence, low efficiency, etc. with a large amount of calculation, and achieves the effect of good calculation stability, reduction of iteration steps, and consideration of efficiency and accuracy.

Active Publication Date: 2021-06-15
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

However, these methods have not completely solved the problems of "large amount of calculation" and "solution of rigidity" in thermochemical non-

Method used

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  • Thermochemical unbalanced multistage gas model adaptive algorithm
  • Thermochemical unbalanced multistage gas model adaptive algorithm
  • Thermochemical unbalanced multistage gas model adaptive algorithm

Examples

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Example Embodiment

[0060] Example 1: OREX Return High Ultrasonic Renugestive Simulation. Computing model and flight test conditions Reference "Yukimitsu Y., Minako Y., CFD and FEM Coupling Analysis of OREXAerothermodynamic Flight Data, AIAA 95-2087, 29th AIAA ThermophysicsConference, June 19-22, 1995 / San Diego, CALIFORNIA, 1995: 1-14. The calculation the analog state is 59.6km in the flying height, from 5561.6m / s, the flow temperature is 248.12k, and the wall temperature is 1519K. Numerical simulation uses a Park chemical model, select the AUSMDV format and MinMod limiter, CFL number 10, and the wall condition is an isometrical non-catalytic wall.

[0061] Such as figure 2 As shown, the calculation residual comparison of the method of the present invention and the existing method is given based on example one, and the abscissa represents the calculation time (T wall ) Unit seconds (s), n 2 For nitrogen, ordinate indicates an average calculation residual (uniform). The existing method is a method...

Example Embodiment

[0062] Example 2: HEG Over - wave wind turbine cylindrical model experiment flow simulation. Calculation and experimental conditions Reference Model "Hannemann K., High Enthalpy Flows in the HEG Shock Tunnel: Experiment andNumerical Rebuilding, AIAA 2003-0978, 41st Aerospace Sciences Meeting andExhibit 6-9 January 2003, Reno, Nevada, 2003: 1-18 ". Numerical simulation uses Dunn-Kang chemical models, and the AUSMDV format and MinMod limiter, CFL number 10, and the wall condition are equivalent.

[0063] Such as image 3 As shown, based on the example 2, the method of calculating the method of the present invention and the existing method represents the number of iterative steps (unnecessary), the ordinate represents the average calculation residual (uniform), Tv in the figure (K The vibration temperature. As a result, the method of the present invention calculates the position of the convergence of approximately 150s in advance, and the calculation is reduced by about 32%. It can be...

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Abstract

The invention discloses a thermochemical unbalanced multistage gas model adaptive algorithm which is mainly used for a numerical simulation process of hypersonic thermochemical unbalanced flow. According to the algorithm, on the basis of thermochemical unbalance characteristics such as thermodynamic modal excitation, dissociation/ionization of high-temperature gas, a segmented gradual approximation simulation strategy from simple to complex is adopted from a physical mechanism, and evolution and step-by-step flow simulation of a calculation gas model are automatically completed according to criteria such as pressure, dissociation degree, temperature and ionization degree; and a self-adaptive simulation process of hypersonic thermochemical unbalanced flow is realized. The algorithm is suitable for various calculation media such as the earth atmosphere, the Mars atmosphere and high-temperature fuel gas, the application range is wide, the calculation stability is good, and the convergence speed can be increased and the calculation efficiency can be greatly improved on the premise that the calculation accuracy is guaranteed.

Description

technical field [0001] The invention relates to the field of aerodynamics, in particular to a numerical calculation method for hypersonic thermochemical non-equilibrium flow. Background technique [0002] Hypersonic vehicles fly in the atmosphere. If the flight speed is high (Mach number above 10), high temperature of thousands to tens of thousands of Kelvin will be generated after the shock wave. Complex physical and chemical phenomena will occur in the high-temperature flow field. Dissociation, recombination, exchange, ionization, multi-level ionization and other chemical reactions, gas molecule translational kinetic energy, vibration energy, electronic energy / electronic binding energy and other thermodynamic mode excitations, forming a mixed multi-component dissociation-ionization-thermodynamically excited gas cloud, And expand backward along the flow direction, forming a sheath around the aircraft, this phenomenon is called the hot gas effect. Since the high temperature...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06F17/12G06F113/08G06F111/10G06F119/14
CPCG06F17/12G06F30/20G06F2111/10G06F2113/08G06F2119/14
Inventor 李鹏丁明松陈坚强赵钟董维中何先耀江涛梅杰
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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