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CFD Aerodynamic Modeling Method for Hypersonic Vehicle

A technology of hypersonic speed and modeling method, applied in the aerospace field, can solve the problems of lack of aerodynamic data calculation methods, inability to obtain aerodynamic models, and no similar patents found

Active Publication Date: 2018-01-12
TIANJIN UNIV
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Problems solved by technology

[0007] Through the search of the prior art, no similar patents were found
Especially for complex hypersonic vehicles, there is a lack of suitable aerodynamic data calculation methods, and a true and credible aerodynamic model cannot be obtained

Method used

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  • CFD Aerodynamic Modeling Method for Hypersonic Vehicle
  • CFD Aerodynamic Modeling Method for Hypersonic Vehicle
  • CFD Aerodynamic Modeling Method for Hypersonic Vehicle

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Embodiment Construction

[0024] The invention can provide a new approach for the calculation of aerodynamic data, and provide a basis for subsequent model application and controller design, thereby providing a guarantee for the safe use of hypersonic aircraft.

[0025] With the development of hypersonic flight technology, a variety of modeling methods have been developed to varying degrees. However, due to the extremely expensive cost of flight tests, unreliable mathematical models have brought potential risks to system design, so it is urgently needed A reliable modeling method ensures that the established hypersonic vehicle model is accurate and valid. The main purpose of the present invention is to provide a complete CFD-based aerodynamic modeling method for hypersonic aircraft. Firstly, the modeling method of points, lines and surfaces of the longitudinal structure of hypersonic vehicle is given, and then the method of meshing the model by using structural grid is introduced. After the boundary co...

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Abstract

The invention relates to the field of modeling of aerocrafts in the aerospace field, in particular to a pneumatic modeling method which is suitable for a hypersonic aerocraft and based on CFD, a feasible thought is provided for pneumatic modeling with high experiment costs, the analysis and design progresses of the hypersonic aerocraft are promoted, a comprehensive and reliable modeling method is provided for development of a novel hypersonic aerocraft model, the development cost is reduced, and great application prospects and economic value are realized. According to the technical scheme, the CFD pneumatic modeling method for the hypersonic aerocraft is composed of three parts, namely the pre-treatment part of carrying out numerical modeling and mesh division, the solver part for calculation and solution and the after-treatment part for carrying out result analysis, wherein the pre-treatment part includes the two sub-parts of building a geometric model and dividing calculation meshes. The CFD pneumatic modeling method for the hypersonic aerocraft is mainly applied to design and manufacturing of aerospace aerocrafts.

Description

technical field [0001] The invention relates to the aircraft modeling problem in the field of aerospace. It mainly involves the calculation of aerodynamic data of hypersonic vehicles. Specifically, it involves CFD aerodynamic modeling methods for hypersonic vehicles. technical background [0002] Hypersonic aircraft refers to aircraft, winged or wingless aircraft that fly faster than five times the speed of sound. Aircraft structure design, material properties, mechanical properties, and the impact of high-speed air fluid on the body are different from projectile aircraft or traditional aircraft. Describing the motion laws of a hypersonic vehicle plays an important role in controller design, so it is necessary to fully consider hypersonic fluid characteristics, engine characteristics, structural elastic characteristics, aerodynamic / propulsion / structural coupling characteristics, actuator characteristics, etc. during the modeling process. [0003] For hypersonic vehicles, ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 宗群尤明曾凡琳常陈陈曲照伟
Owner TIANJIN UNIV
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