Hypersonic aerocraft leading edge fluid-heat-solid integrated calculation method

A calculation method and hypersonic technology, applied in calculation, instrumentation, design optimization/simulation, etc., can solve the problems of cumbersome data exchange and calculation amount, and achieve small calculation amount and grid dependence, good stability and calculation accuracy Effect

Inactive Publication Date: 2018-03-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a hypersonic vehicle leading edge flow-heat-solid integrated calculation method to solve the problem of flow field

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Embodiment Construction

[0064] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and the drawings, and the content mentioned in the embodiments does not limit the present invention.

[0065] 1. Technical parameters

[0066] Wieting.AR (Allen RW 1987NASA TM-100484) completed the aerodynamic heating test of the leading edge of a stainless steel round tube in the 8-foot high enthalpy wind tunnel of the NASA Langley Research Center in the United States in 1987 (Wieting AR, Holden M S1987AIAA 22nd Thermophysics Conference Honolulu Hawaii June 8-10, 1987), the test has been used many times to verify the accuracy of the heat transfer coupling calculation of the flow field structure. The present invention also selects infinite-length stainless steel round pipe models with exactly the same conditions, and the size of the round pipe is the outer diameter R out =0.0381m, inner diameter R in =0.0254m, the s...

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Abstract

The invention discloses a hypersonic aerocraft leading edge fluid-heat-solid integrated calculation method, and belongs to the field of aerocraft pneumatic calculation. For solving the problem of complex coupling of structure heat transfer and hypersonic speed flow aerodynamic heating, the method avoids the complex data exchange and calculation amount caused by flow field and structure coupling alternate iteration calculation performed within a time domain through a traditional aerodynamic heating/structure heat transfer coupling solving method, the flow field and the structure are adopted asa physical field, and a uniform control equation is adopted. Physical parameters of a fluid and solid interface are defined again, a finite volume method is performed on a full physical field for spatial dispersion, and hidden time iteration is adopted for time stepping. Compared with a coupling algorithm, the method needs no extra data exchange or coupling strategy, the calculation result and anexperiment value are closer, the calculation amount and the grid dependency are smaller, and the better stability and calculation precision are achieved.

Description

Technical field [0001] The invention belongs to the technical field of aircraft aerodynamic calculation, and specifically refers to a hypersonic aircraft leading edge flow-heat-solid integrated calculation method. Background technique [0002] Hypersonic flow usually refers to flow with a Mach number greater than 5. When the aircraft enters and exits the atmosphere at hypersonic speed or continues to fly in space, due to the compression effect and the intense friction between the aircraft surface and the air (Wang Jiangfeng, Wu Yizhao, Ji Weidong, Fan Xiaofeng, Zhao Faming, Lu Zhenjun 2015 "Acta Aeronautica Sinica" 36(1):159- 175 "Research Progress in Numerical Methods for Hypersonic Complicated Aerodynamic Problems"), the head of the aircraft, the leading edge of the air inlet and other key parts will be subjected to huge aerodynamic heating, which will produce strong aerodynamic force, aerodynamic heat and structural coupling problems, which is safe for flight Bring great hidd...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 李佳伟王钰涵杨天鹏王江峰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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