CN112613117B - Rapid construction and design method for aviation flap from unfolding size to 3D - Google Patents
Rapid construction and design method for aviation flap from unfolding size to 3D Download PDFInfo
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- CN112613117B CN112613117B CN202011439712.5A CN202011439712A CN112613117B CN 112613117 B CN112613117 B CN 112613117B CN 202011439712 A CN202011439712 A CN 202011439712A CN 112613117 B CN112613117 B CN 112613117B
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The application relates to the technical field of airplane digital manufacturing, and discloses a design method for quickly constructing an aviation flap from an unfolding size to 3D, which specifically comprises the following steps: a, optimizing a theoretical outline curved surface of an airplane to realize expansion of the curved surface; b, determining a theoretical outline curved surface, an assembly position and an unfolding positioning reference of the part, and generating an unfolding dimension line part outline on the unfolding curved surface; and C, rapidly, reversely and correctly folding the optimized part shape unfolding curved surface to a theoretical curved surface so as to obtain the hyperbolic theoretical shape surface member part three-dimensional digital model. The method and the device guarantee the assembly quality and the assembly efficiency of the parts, and simultaneously improve the modeling efficiency during working.
Description
Technical Field
The application relates to the technical field of airplane digital manufacturing, in particular to a design method for quickly constructing an aviation flap from an unfolding size to 3D.
Background
At present, in the project engineering of three-dimensional digital model construction, the expression modes of the shape of a large number of flaps (non-standard type flaps and standard type flaps) are all the unfolding sizes, and the three-dimensional digital model is an entity model based on the theoretical shape curved surface of an airplane. The theoretical appearance curved surface of aircraft mostly is the broken surface constitution of double curvature distortion, if design according to central normal direction projection plane, then the great problem of appearance deviation can appear, even follow-up after the spline arrangement, also have great deviation, be not conform to the design size and the design theory of product drawing to still there is the problem of consuming time length and inefficiency.
The design method in the prior art will finally affect the quality of the parts, the subsequent assembly of the parts and the assembly efficiency, so that the design method of the parts needs to be re-optimized and defined, and the three-dimensional digital model which meets the design size and design concept of the product drawing can be rapidly and qualitatively completed.
Disclosure of Invention
In order to solve the problems and the defects in the prior art, the application provides a rapid construction and design method of the aviation flap from the unfolding size to 3D, so that the assembly quality and the assembly efficiency of parts are ensured, and meanwhile, the modeling efficiency during working is also improved.
In order to achieve the above object, the technical solution of the present application is as follows:
a design method for quickly constructing an aviation flap from an unfolding size to a 3D mode is characterized in that: the method specifically comprises the following steps:
step A, optimizing a hyperbolic theoretical outline curved surface of the airplane to expand the curved surface;
b, determining a hyperbolic theoretical outline curved surface, an assembly position and an unfolding positioning reference of the part, and generating an unfolding dimension line part outline on an unfolding curved surface;
and step C, rapidly, reversely and correctly folding the part shape unfolding curved surface after optimization to the hyperbolic theoretical shape curved surface so as to form the three-dimensional digital model of the part with the hyperbolic theoretical shape curved surface.
Preferably, the step a specifically includes the steps of:
a1, intercepting a hyperbolic theoretical outline curved surface according to the approximate outline shape of a part;
a2, extracting characteristic outline lines of a hyperbolic theoretical outline curved surface according to the part outline definition, and smoothing the outline lines;
step A3, reconstructing a hyperbolic theoretical outline curved surface according to the smoothed outline;
and A4, checking the reconstruction accuracy of the curved surface, wherein the deviation between the reconstructed curved surface and the original curved surface is in accordance with the manufacturing requirement of the part.
Preferably, the step C includes obtaining the required part curved profile using the folded item in the size transfer module.
Preferably, in the step a1, the hyperbolic theoretical profile surface is cut to be larger than the part profile.
The beneficial effect of this application:
the method and the device realize perfect combination of the covering cover and the covering part, ensure the assembly quality and the use efficiency of the part, simultaneously improve the modeling efficiency and promote the rapid reconstruction quality of the digital model of the aviation product based on the drawing.
Detailed Description
The technical solutions for achieving the objects of the present invention are further described below by specific examples, and it should be noted that the technical solutions claimed in the present application include, but are not limited to, the following examples.
The embodiment discloses a method for quickly constructing and designing an aviation flap from an unfolding size to a 3D (three-dimensional) mode, which specifically comprises the following steps:
step A, optimizing a hyperbolic theoretical outline curved surface of the airplane to expand the curved surface;
b, determining a hyperbolic theoretical outline curved surface, an assembly position and an unfolding positioning reference of the part, and generating an unfolding dimension line part outline on an unfolding curved surface;
and C, rapidly, reversely and correctly folding the part shape unfolding curved surface to the hyperbolic theoretical shape curved surface through the optimized part shape unfolding curved surface so as to form the part three-dimensional digital model by the hyperbolic theoretical shape curved surface.
Further, step a further comprises the following steps:
a1, intercepting a hyperbolic theoretical outline curved surface according to the approximate outline shape of a part;
step A2, extracting characteristic outline lines of theoretical outline curved surfaces according to part outline definition because the theoretical outline curved surfaces of the airplane have more broken surfaces and gaps among the curved surfaces and cannot be unfolded, and smoothing the outline lines; modifying the node positions of the spline curves by using a smooth curve tool in CATIA software to ensure that the curves are continuous and the curvature change is smooth and smooth, and eliminating appearance mutation;
step A3, reconstructing a hyperbolic theoretical outline curved surface according to the smoothed outline, and optimizing the multi surface into a single surface;
and A4, checking the reconstruction accuracy of the curved surface, wherein the deviation between the reconstructed curved surface and the original curved surface is in accordance with the manufacturing requirement of the part.
Further, in step a1, the hyperbolic theoretical profile surface is cut out to be larger than the part profile.
Further, step C includes obtaining the required part curved profile using the folding item in the CATIA software dimension transfer module.
In the description of the present application, it is further noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
The foregoing is directed to embodiments of the present invention, which are not limited thereto, and any simple modifications and equivalents thereof according to the technical spirit of the present invention may be made within the scope of the present invention.
Claims (3)
1. A design method for quickly constructing an aviation flap from an unfolding size to a 3D mode is characterized in that: the method specifically comprises the following steps:
step A, optimizing a hyperbolic theoretical outline curved surface of the airplane to expand the curved surface;
b, determining a hyperbolic theoretical outline curved surface, an assembly position and an unfolding positioning reference of the part, and generating an unfolding dimension line part outline on an unfolding curved surface;
c, rapidly, reversely and correctly folding the part shape unfolding curved surface to the hyperbolic theoretical shape curved surface through the optimized part shape unfolding curved surface so as to construct a part three-dimensional digital model by the hyperbolic theoretical shape curved surface;
the step A specifically comprises the following steps:
a1, intercepting a hyperbolic theoretical outline curved surface according to the approximate outline shape of a part;
a2, extracting characteristic outline lines of a hyperbolic theoretical outline curved surface according to the part outline definition, and smoothing the outline lines;
step A3, reconstructing a hyperbolic theoretical outline curved surface according to the smoothed outline;
and step A4, checking the reconstruction accuracy of the curved surface, wherein the deviation between the reconstructed curved surface and the original curved surface is in accordance with the manufacturing requirement of the part.
2. The rapid construction and design method of the aviation flap from the unfolding size to the 3D according to claim 1, characterized in that: and the step C comprises the step of obtaining the required curved surface profile of the part by using the folding item in the size transfer module.
3. The rapid construction and design method of the aviation flap from the unfolding size to the 3D according to claim 1, characterized in that: in the step A1, the intercepted hyperbolic theoretical shape curved surface is larger than the part shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011439712.5A CN112613117B (en) | 2020-12-11 | 2020-12-11 | Rapid construction and design method for aviation flap from unfolding size to 3D |
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| CN202011439712.5A CN112613117B (en) | 2020-12-11 | 2020-12-11 | Rapid construction and design method for aviation flap from unfolding size to 3D |
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| CN112613117A CN112613117A (en) | 2021-04-06 |
| CN112613117B true CN112613117B (en) | 2022-08-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112560190A (en) * | 2020-12-28 | 2021-03-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Dimension reduction design method for special-shaped curved surface functional structure |
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