Body propelling integrated outer appearance modeling process for supersonic aircraft

A technology of hypersonic speed and modeling method, which is applied in 3D modeling, instrumentation, image data processing, etc., can solve the problems of inconvenient adoption, complex geometric shape of the aircraft, and no systematic solution for the parameterization of the geometric shape of the aircraft. Simplicity of the modeling process

Inactive Publication Date: 2009-07-08
BEIHANG UNIV
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Problems solved by technology

[0004] At present, in the field of hypersonic vehicle design and development at home and abroad, there are two main problems in the geometric modeling of hypersonic vehicles. Complete design parameters that can drive geometric changes are not easy to adopt in the overall design and multidisciplinary design optimization process; second, it does not reflect the characteristics of the integration of propulsion of the fuselage of a hypersonic aircraft, only explaining the generation method of the entire aircraft shape, not reflecting Influence of the flow pattern of the propulsion system on the shape of th

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  • Body propelling integrated outer appearance modeling process for supersonic aircraft
  • Body propelling integrated outer appearance modeling process for supersonic aircraft
  • Body propelling integrated outer appearance modeling process for supersonic aircraft

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[0046] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0047] The design flow chart of its modeling method is as follows: figure 1 As shown, the specific steps are as follows:

[0048] (1) Design the geometric profile of the two-dimensional flow channel of the propulsion system

[0049] Under the constraint of the total length of the aircraft, the design of the flow channel of the propulsion system of the hypersonic aircraft, including the precursor inlet ( figure 2 1 in), combustion chamber ( figure 2 2 in), rear body nozzle ( figure 2 3) in three parts. The precursor inlet is composed of multiple compression wedges; the combustion chamber is composed of equal-section isolation sections ( figure 2 4) and expansion segment ( figure 25) in the composition; the rear body nozzle is in the form of a curve. The flow channel of the entire propulsion system forms the lower surface of the hypersonic vehicle, ...

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Abstract

A method for modeling a fuselage of a hypersonic aircraft by promoting outline integration comprises the following eight steps: 1, designing a geometric molding surface of a two-dimensional flow channel of a propulsion system; 2, designing a view-from-above contour curve of the fuselage of the aircraft; 3, designing a side-view contour curve of the fuselage of the aircraft; 4, designing section forms of longitudinal main station positions of the fuselage of the aircraft and variation modes of control parameters; 5, generating a three-dimensional fuselage of the aircraft; 6, generating a three-dimensional supersonic combustion ramjet hood; 7, designing an outline drawing of wing surfaces, and generating three-dimensional wing surfaces; and 8, generating a promotion integrated outline of the three-dimensional fuselage by assembling the fuselage, the ramjet hood and all the wing surfaces. The method has the advantage of simple and rapid modeling process, achieves the effect of promoting integration of the fuselage of the hypersonic aircraft, and is capable of improving paces and efficiencies in designing, developing and manufacturing the hypersonic aircraft.

Description

(1) Technical field: [0001] The invention relates to a shape modeling method, in particular to a hypersonic aircraft fuselage propulsion integrated shape modeling method, which belongs to the field of design and development of hypersonic aircraft. (two) background technology: [0002] The hypersonic vehicle with the scramjet engine and its combined power engine as the propulsion system has the characteristics of high-speed flight above Mach 5, and can be widely used in fast-response missiles, global reconnaissance and reusable space vehicles. This type of aircraft has the characteristics of the integration of the fuselage and the propulsion system. The aircraft fuselage and engine propulsion system cannot be designed and developed separately like traditional aircraft, but must be designed and developed synchronously under the premise of integration. [0003] Specifically, the fuselage propulsion integration of a hypersonic vehicle means that the front body of the aircraft is...

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Application Information

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IPC IPC(8): G06T17/40G06T19/00
Inventor 徐大军蔡国飙徐旭陈兵
Owner BEIHANG UNIV
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