Fluid-solid-heat rapid calculation method for high-speed aircrafts with three-dimensional complicated appearances

A high-speed aircraft and fast computing technology, applied in computing, computer-aided design, instruments, etc., can solve problems such as high computing cost, low efficiency, and long cycle

Active Publication Date: 2018-03-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0006] Aiming at the deficiencies of the above-mentioned prior art, the object of the present invention is to provide a fast fluid-solid-heat calculation method for a three-dimensional complex shape high-speed

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  • Fluid-solid-heat rapid calculation method for high-speed aircrafts with three-dimensional complicated appearances
  • Fluid-solid-heat rapid calculation method for high-speed aircrafts with three-dimensional complicated appearances
  • Fluid-solid-heat rapid calculation method for high-speed aircrafts with three-dimensional complicated appearances

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Embodiment Construction

[0087] 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 accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0088] 1. RAMC-II is heated for a long time in cruising state (high temperature non-equilibrium effect)

[0089] 1.1 Technical parameters

[0090] The calculated shape adopts the typical high-speed aircraft RAMC-II spherical cone test model, and its geometric parameters are: the radius of curvature of the head is 0.152m, the half-vertex angle is 9°, and the length of the model is 1.3m. The calculation grid of the inviscid external flow field solution is a block structure grid with a total number of elements of about 400,000 and an object surface element of about 15,000. The set cruise state is: Ma ∞ =12, angle of attack α=0°, flight altitude H=33km, flight time t=1000s.

[0091] Structura...

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Abstract

The invention discloses a fluid-solid-heat rapid calculation method for high-speed aircrafts with three-dimensional complicated appearances, and belongs to the field of aircraft pneumatic calculation.According to the method, static aerodynamic heat calculation is simplified to inviscid outflow numerical solution and boundary layer inner heat flow solution by adoption of a CFD numerical calculation and engineering algorithm combined method according to a boundary layer theory, and anti-heat system structure heat transfer calculation model is coupled at the same time. According to the method, advantages of overall length numerical simulation and an engineering algorithm are combined, so that an aircraft whole surface heat flow density and anti-heat structure temperature field time-variant characteristics can be rapidly and efficiently given to a method for calculating pneumatic heating and structure coupling heat transfer characteristics of aircrafts with three-dimensional complicated appearances under multiple flight states, the gaps such as high calculation cost, low efficiency and long period of numerical simulation method are filled, and the application range of the engineeringalgorithm is broadened at the same time.

Description

technical field [0001] The invention belongs to the technical field of aircraft aerodynamic calculation, and specifically refers to a fast fluid-solid-heat calculation method for a high-speed aircraft with a three-dimensional complex shape. Background technique [0002] When a hypersonic vehicle continues to fly in the atmosphere, the surface of the vehicle will bear huge aerodynamic heat (Wang Jiangfeng, Wu Yizhao. Research progress on numerical methods for hypersonic complex aerodynamic problems[J].Acta Aeronautics Sinica.2015,33(1):159-175) . Aerodynamic heat will lead to an increase in the temperature of the aircraft structure, changing the temperature field distribution in the structure, thereby changing the physical properties of the structural material, and the change in the properties of the structural material will cause changes in the structural stiffness and structural mode, which will greatly affect the flight safety of the aircraft. Hidden danger. Therefore, t...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2119/08Y02T90/00
Inventor 李佳伟杨天鹏王江峰王钰涵李龙飞王丁
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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