Prediction and control method for separation process of hypersonic aircraft under action of two-phase flow field

A hypersonic, separation process technology, applied in the direction of electric controllers, controllers with specific characteristics, etc.

Active Publication Date: 2020-03-10
CHINA ACAD OF LAUNCH VEHICLE TECH
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AI Technical Summary

Problems solved by technology

[0003] The technical problem of the present invention is: the present invention proposes an accurate prediction and active control method for the separation process of a hypersonic statically unstable aircraft under the action of a two-phase flow field, with the purpose of solving the problem of separation design of a hypersonic aircraft under the complex aerodynamic interference

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  • Prediction and control method for separation process of hypersonic aircraft under action of two-phase flow field
  • Prediction and control method for separation process of hypersonic aircraft under action of two-phase flow field
  • Prediction and control method for separation process of hypersonic aircraft under action of two-phase flow field

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Embodiment Construction

[0036] The present invention will be described in detail below in conjunction with the accompanying drawings and examples.

[0037] 1. Grid establishment

[0038] According to the geometric information of the aircraft and the separated body, the partitioned overlapping grid required for the separated aerodynamic CFD calculation is established.

[0039] The partitioned overlapping grid method is a discretization method for structural space. It divides the complex flow area into sub-areas with relatively simple geometric boundaries. The calculation grids in each sub-area are independently generated, and there is an overlapping or nesting relationship with each other. The flow field information is matched and coupled at the boundary of the overlapping area through interpolation. The overlapping grid method can easily deal with various complex flow field structures, and is especially suitable for flow field calculations with complex shapes and relative motion of objects. After ea...

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Abstract

The invention discloses a prediction and control method for a separation process of a hypersonic aircraft under the action of a two-phase flow field. The prediction method is realized by the followingsteps: discretizing the flow field of a hypersonic aircraft by adopting an overlapping grid method, carrying out equivalent correction on kinetic energy and momentum of the fluid through thrust reverser rocket inner fluid equivalent to air, establishing an N-S equation of the flow field after equivalence, carrying out flow field CFD calculation according to the established N-S equation of the equivalent flow field to obtain the aerodynamic force and moment borne of the separated bodies in the separation process and solving separation motion under different working conditions by utilizing theobtained aerodynamic force and moment borne of the separated body to obtain centroid motion and attitude motion parameters of the separated body, wherein the separated body comprises a front body anda rear body.

Description

technical field [0001] The invention belongs to the field of aircraft separation design, and is a high-precision simulation analysis method for the separation process of a hypersonic aircraft in the atmosphere. Background technique [0002] With its unique advantages, hypersonic vehicles are gradually becoming a research hotspot in the fields of aerospace transportation, military offensive and defensive games, etc. Due to its hypersonic flight in the atmosphere, its separation process faces an extremely harsh environment. The influence of factors such as large dynamic pressure and jet flow interference makes its separation flow field extremely complex, and it is coupled with the separation movement, making it difficult to predict the separation process. The traditional separation design method, using the steady aerodynamic data interpolation table as the basis for the separation simulation calculation, has been unable to meet the requirements of reliable separation design fo...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42
CPCG05B11/42Y02T90/00
Inventor 祝学军赵长见赵俊锋陈轶迪方平宋志国涂建秋罗波蔡强何佳马奥家王晨曦杨鸿俊
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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