A mesh generation method for aerothermal numerical calculation of hypersonic return capsule shape
A hypersonic, numerical computing technology, used in computing, electrical digital data processing, special data processing applications, etc., to achieve the effect of ensuring calculation accuracy, improving calculation efficiency, and ensuring flow resolution
Active Publication Date: 2017-11-07
CHINA ACAD OF AEROSPACE AERODYNAMICS
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[0004] The problem to be solved by the present invention is: based on the mature numerical simulation technology framework and overcoming the deficiencies of the prior art, a grid generation method for the numerical calculation of aerodynamic heat of the shape of the hypersonic return capsule is proposed, and the specific grid generation process and The value range of key parameters in the grid generation process realizes the quantitative generation technology of high-quality grids for aerodynamic and thermal prediction of the shape of the return cabin. Numerical Simulation Accuracy
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[0034] The return cabin includes a large bottom, a corner, a cabin body and a bottom. The big bottom is a spherical crown structure, and the cabin body is an inverted conical hollow structure. The big bottom and the end face with a large opening of the cabin body are connected by a corner. The bottom is fixedly connected to the end face with the smaller opening of the cabin body, and the diameter of the circular plate structure at the bottom is the same as the diameter of the end face with the smaller opening of the cabin body;
[0035] The return cabin has an axisymmetric structure, and is symmetrical about any plane passing through the axis of symmetry. Half of the intersection line between the plane passing through the axis of symmetry and the outer contour of the return cabin is the geometric bus line. The geometric bus line mainly includes the outsole curve, the corner curve, and the inverted cone. Curve and bottom curve, the outsole curve, corner curve, inverted cone curv...
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Provided is a hypersonic speed re-entry capsule shape aerodynamic heat value computational grid generating method. The method comprises the steps that, firstly, a stagnation point thermal flow and a reference thermal flow are calculated according to an incoming flow condition and a hypersonic speed re-entry capsule undersole radius, and a first layer grid height in an object plane normal direction of a re-entry capsule is confirmed; and then grid points are arranged on a geometrical generatrix of the re-entry capsule; an internal layer grid is generated by using a hyperbolic method; finally, the outer boundary of an external layer grid is generated by using a front distance, a back distance and the grid height, and the external layer grid is generated by adopting an ellipse method. According to the method, a grid generating process and a specific value range of key parameters during a grid generating procedure are provided, a quantification generating technology of a re-entry capsule shape aerodynamic heat prediction high quality grid is achieved, the influence by human factors is maximally reduced, and the value simulation precision of the re-entry capsule shape aerodynamic heat prediction is fully guaranteed.
Description
technical field [0001] The invention relates to a method for generating an aerothermal numerical calculation grid, in particular to a method for generating a hypersonic return cabin shape aerothermal numerical calculation grid, belonging to the technical field of hypersonic aerothermal numerical simulation. Background technique [0002] With the further development of manned spaceflight, lunar exploration project and deep space exploration, the heat protection design of the return capsule has gradually become the core key technology. Due to the high bluntness of the large bottom and small curvature corners in the return capsule, it is difficult for the traditional engineering rapid prediction method based on the boundary layer theory to accurately give the results of the aerodynamic and thermal environment. Numerical simulation technology is an important means to solve this problem. Due to the hypersonic speed and high bluntness, numerical simulation technology also has grea...
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IPC IPC(8): G06F17/50
Inventor 张亮李齐江娟施家桐姜宝森耿云飞陈智苗文博张学军程晓丽
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS