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Polyhedral cone configuration flight wind tunnel standard model layout and design method

A design method and configuration technology, applied in design optimization/simulation, special data processing applications, geometric CAD, etc.

Active Publication Date: 2020-11-27
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, domestic related research is still in its infancy in terms of test model layout design for model flight tests, and the layout and configuration of aircraft that are convenient for flight test testing and measurement need to be developed urgently

Method used

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  • Polyhedral cone configuration flight wind tunnel standard model layout and design method
  • Polyhedral cone configuration flight wind tunnel standard model layout and design method
  • Polyhedral cone configuration flight wind tunnel standard model layout and design method

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Embodiment 1

[0080] According to step 1, the design length of the given test model is L=1638mm, and the total number of segments K=6. The length dimensions of each segment configuration are L 1 =8.628mm,L 2 =191.372mm, L 3 =150mm,L 4 =250mm,L 5 =500mm,L 6 =553mm. The half-cone angles of each segment configuration are θ 1 =10.68°, θ 2 =10.68°, θ 3 =11.94°, θ 4 =9.01°, θ 5 =4.53°, θ 6 =4.53°. The above-mentioned design parameters satisfy formulas (1)-(3).

[0081] According to step 2, the number of sides of a given regular polygon is N=4. Given dimensionless parameters a = 634.429, b = 117.214. According to formula (4), c=165.766 can be obtained. According to formula (6) can get R oc =375. It is easy to know that a-2b=400. Thus, the proportional relationship of each length parameter in the cross-sectional shape is obtained.

[0082] According to step 3, the coordinate system O required for the basic shape design can be defined xyzi (1≤i≤6).

[0083] According to step 4, ...

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Abstract

The invention discloses a polyhedral cone configuration flight wind tunnel standard model layout and design method. The appearance of the test model is a polyhedral cone structure which is provided with a control tail wing and provided with a plurality of large plane structures, the polyhedral cone structure comprises a plurality of sections along the axis, the first section is a ball head structure formed by cutting a plurality of planes, the middle sections are polygonal skirt structures, and the last section is a cylinder structure formed by cutting a plurality of planes. The method is based on a parameterization thought, a non-regular polyhedral cone configuration is adopted as a basic shape, and the whole shape can be completely analyzed and described by a mathematical expression so as to meet the requirement of a flight test on simplification of aerodynamic layout. Due to the fact that parameterized expression is adopted in the method, the designed test model can be optimized andadjusted according to overall, pneumatic and test requirements. The tail section of the flight test model designed by the adopting method is provided with a pneumatic control surface which is arranged in an X shape and has a right-angled trapezoidal plane shape, and the control surface can be optimally designed according to actual flight requirements, so that the test model realizes autonomous controllable flight for a certain period of time.

Description

technical field [0001] The invention relates to the technical field of aerodynamic layout design of aircraft, in particular to a multi-faceted cone configuration flight test standard model layout and design method that can be used for the research on basic problems of hypersonic flow. Background technique [0002] Model flight test (also known as "flying wind tunnel") is one of the three major means of aerodynamics research (the other two are computer numerical simulation and ground wind tunnel experiment), and it has an irreplaceable role in obtaining aerodynamic data in real flight environments. important role. With the continuous development of aerodynamics research in my country, especially hypersonic aerodynamics research, more and more basic problems of flow (such as aerodynamics / heat of complex shape aircraft, high-temperature real gas effects, multi-scale cross-basin flow, boundary Layer transition, shock wave-boundary layer interference, high-enthalpy boundary layer...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20Y02T90/00
Inventor 罗磊贾洪印吴晓军周桂宇欧朝吉洪亮刘深深张培红张耀冰赵炜龚小权唐静张健
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT