CN106709184B - Method for generating inner curved surface of wing panel - Google Patents
Method for generating inner curved surface of wing panel Download PDFInfo
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- CN106709184B CN106709184B CN201611216460.3A CN201611216460A CN106709184B CN 106709184 B CN106709184 B CN 106709184B CN 201611216460 A CN201611216460 A CN 201611216460A CN 106709184 B CN106709184 B CN 106709184B
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Abstract
The invention discloses a method for generating an inner curved surface of a wing wallboard, which is characterized in that wallboard inner data are stored in an Excel table according to a self-defined format, accurate wallboard, beam and stringer inner curved surfaces are rapidly generated according to a specified mode in a Catia environment through original data, and when the appearance of a wing is a ruled surface or a hyperboloid and the thickness of the inner curved surface between every two stringers changes linearly along the spanwise direction, a first step is selected to generate the wing wallboard inner curved surface; when the wing appearance is a ruled surface or a hyperboloid and the thickness of the inner shape surface between every two stringers changes nonlinearly along the span direction, generating the inner shape curved surface of the wing wallboard by the second step; when the thickness change of the inner shape surface changes along the unfolding direction and the chord direction in a non-linear way, the inner shape curved surface of the wing wall plate is generated in the selection step three times, and the modeling efficiency and the modeling precision of the inner shape of the wall plate are greatly improved.
Description
Technical Field
The invention belongs to the technical field of aircraft structure modeling, and particularly relates to a method for generating an inner-shaped curved surface of a wing wall plate.
Background
At present, the models of domestic airplanes are various, the inner shape of a wing wall plate is more and more complex, and manual modeling or a programming mode aiming at a specific model is generally adopted for solving the problem. The disadvantages of this approach are: the design has no unified standard, the inner shape errors brought by different personnel and different modeling modes are different, the updating is very complicated and time-consuming, and manual or reprogramming modeling is still needed during the design of a new model.
Disclosure of Invention
The purpose of the invention is as follows: the method for generating the inner-shaped curved surface of the wing wall plate is provided for solving the problems of non-uniformity, complexity and time consumption in the prior art.
The technical scheme is as follows:
the method for generating the inner curved surface of the wing panel is characterized in that the inner data of the panel is stored in an Excel table according to a self-defined format, the accurate inner curved surfaces of the panel, a beam and a stringer are rapidly generated in a Catia environment according to an appointed mode through original data, and when the appearance of the wing is a ruled surface or a hyperboloid and the thickness of the inner curved surface between every two stringers changes linearly along the spanwise direction, the inner curved surface of the wing panel is generated by a first step; when the wing appearance is a ruled surface or a hyperboloid and the thickness of the inner shape surface between every two stringers changes nonlinearly along the span direction, generating the inner shape curved surface of the wing wallboard by the second step; when the thickness change of the inner shape surface changes in a nonlinear way along the spanwise direction and the chordwise direction, the generation of the inner shape curved surface of the wing wall plate is carried out in the selection step three, and the specific steps are as follows:
the method comprises the following steps: establishing a thickness line at the boundary along the direction of the appearance normal for each linearly-changed curved surface block between the two stringers, establishing an inner shape surface boundary line and a guide line by taking the thickness line as the boundary and the outer shape surface as the guide, and establishing an inner shape surface by taking the inner shape surface boundary line and the guide line as the reference; according to the method, the inner curved surface of each linear change area is created. The complete curved surface between the two stringers from the wing root to the wing tip is spliced by the inner-shaped curved surface blocks, and each two inner-shaped curved surface blocks are continuous in a first order at the boundary;
step two: establishing a thickness line at each rib position between the two stringers along the direction of the appearance normal, establishing an inner profile surface section line and a guide line by taking the thickness line as a boundary and taking an outer profile curved surface as a guide, and establishing a complete curved surface between the two stringers from the wing root to the wing tip by taking the section line of the inner profile surface and the guide line as a reference, wherein the curved surface is smooth and continuous in a second order at each rib position;
step three: establishing a thickness line at the intersection point of each stringer and each rib along the direction of the profile normal, and establishing a guide line of an inner profile at each stringer by taking the thickness line as a boundary and taking an outer profile curved surface as a guide; at each rib position, taking the thickness line as a boundary and taking the outer-shaped curved surface as a guide to create a section line of the inner-shaped surface; then, a complete inner-shaped curved surface is created by taking the section lines and the guide lines of the inner-shaped surface as reference, and the curved surface is smooth and continuous in the second order at each control point.
Advantageous effects
The invention greatly improves the efficiency and the precision of the modeling of the inner shape of the wall plate and generates practical benefits.
Drawings
Fig. 1 is a schematic diagram of a step-specific forming process according to a first embodiment of the present invention.
Fig. 2 is a schematic diagram of the third step of the present invention.
Detailed Description
The present invention is described in further detail below.
The method for generating the inner curved surface of the wing panel is characterized in that the inner data of the panel is stored in an Excel table according to a self-defined format, the accurate inner curved surfaces of the panel, a beam and a stringer are rapidly generated in a Catia environment according to an appointed mode through original data, and when the appearance of the wing is a ruled surface or a hyperboloid and the thickness of the inner curved surface between every two stringers changes linearly along the spanwise direction, the inner curved surface of the wing panel is generated by a first step; when the wing appearance is a ruled surface or a hyperboloid and the thickness of the inner shape surface between every two stringers changes nonlinearly along the span direction, generating the inner shape curved surface of the wing wallboard by the second step; when the thickness change of the inner shape surface changes in a nonlinear way along the spanwise direction and the chordwise direction, the generation of the inner shape curved surface of the wing wall plate is carried out in the selection step three, and the specific steps are as follows:
the method comprises the following steps: establishing a thickness line at the boundary along the direction of the appearance normal for each linearly-changed curved surface block between the two stringers, establishing an inner shape surface boundary line and a guide line by taking the thickness line as the boundary and the outer shape surface as the guide, and establishing an inner shape surface by taking the inner shape surface boundary line and the guide line as the reference; according to the method, the inner curved surface of each linear change area is created. The complete curved surface between the two stringers from the wing root to the wing tip is spliced by the inner-shaped curved surface blocks, and each two inner-shaped curved surface blocks are continuous in a first order at the boundary; as shown in fig. 1, each two inside shape surface blocks are first order continuous at the boundary EK.
The method has the advantages that: in the process of creating the boundary line and the lead line of the inner-shaped curved surface, the boundary line and the lead line are always associated with the shape, the thickness of the inner-shaped surface is accurate, the data volume is small, and only the thickness of the rib position of the end point of linear change needs to be given, so that the updating is convenient. Meanwhile, the inner shape surface changes uniformly, and the weight is lighter. The current numerical control machining level can also conveniently finish the inner shape. The disadvantages are that: a linear fit to the finite element calculated thickness data is required.
Step two: establishing a thickness line at each rib position between the two stringers along the direction of the appearance normal, establishing an inner profile surface section line and a guide line by taking the thickness line as a boundary and taking an outer profile curved surface as a guide, and establishing a complete curved surface between the two stringers from the wing root to the wing tip by taking the section line of the inner profile surface and the guide line as a reference, wherein the curved surface is smooth and continuous in a second order at each rib position;
the method has the advantages that: in the process of creating the boundary line and the lead line of the inner-shaped curved surface, the boundary line and the lead line are always related to the outer shape, and the thickness of the inner-shaped surface is accurate. Meanwhile, the inner shape surface changes uniformly, and the weight is lighter. The disadvantages are that: the data volume of the inner shape surface is large, the inner shape surface is difficult to describe in the traditional two-dimensional drawing, and a three-dimensional digital model needs to be provided for a manufacturing party.
Step three: establishing a thickness line at the intersection point of each stringer and each rib along the direction of the profile normal, and establishing a guide line of an inner profile at each stringer by taking the thickness line as a boundary and taking an outer profile curved surface as a guide; at each rib position, taking the thickness line as a boundary and taking the outer-shaped curved surface as a guide to create a section line of the inner-shaped surface; the complete inner curve is then created, based on the section lines and guide lines of the inner curve, which is a second order smooth continuation at each control point, as shown in fig. 2.
The method has the advantages that: in the process of creating the boundary line and the lead line of the inner-shaped curved surface, the boundary line and the lead line are always related to the outer shape, and the thickness of the inner-shaped surface is accurate. Meanwhile, the inner shape surface changes uniformly, and the weight is lighter. The disadvantages are that: the data volume of the inner shape surface is large, the inner shape surface is difficult to describe in the traditional two-dimensional drawing, and a three-dimensional digital model needs to be provided for a manufacturing party.
The first embodiment is as follows:
the specific application process of the method is described below by taking an ARJ21 airplane as an example.
ARJ21 the wing is a hyperboloid wing type, and the thickness data of the inner shape surface changes along the spanwise direction, so the first step forming method is adopted.
For each linearly changing curved surface block between two stringers at ARJ21, a thickness line is established along the profile normal direction at the boundary, then an inner profile boundary line and a guide line are created using the thickness line as the boundary and the outer profile as the guide, and then an inner profile curved surface is created using the inner profile boundary line and the guide line as the reference. According to the principle, the inner curved surface of each linear change area is created. The complete curved surface from the wing root to the wing tip between the two stringers is spliced out by the inner curved surface blocks, as shown in fig. 1. The inner profile between all stringers together comprises ARJ21 an aircraft wing panel inner profile.
The internal shapes of the wing wall plates generated by the multiple models through the method meet the design requirement of the internal shapes of the wall plates, and play an important role in unifying the design standard and improving the design efficiency.
Claims (1)
1. The method for generating the inner curved surface of the wing panel is characterized in that the inner data of the panel is stored in an Excel table according to a self-defined format, the accurate inner curved surface of the panel, a beam or a stringer is rapidly generated in a Catia environment according to an appointed mode through original data, and when the appearance of the wing is a ruled surface or a hyperboloid and the thickness of the inner curved surface between every two stringers linearly changes along the spanwise direction, the inner curved surface of the wing panel is generated by a first step; when the wing appearance is a ruled surface or a hyperboloid and the thickness of the inner shape surface between every two stringers changes nonlinearly along the span direction, generating the inner shape curved surface of the wing wallboard by the second step; when the thickness change of the inner shape surface changes in a nonlinear way along the spanwise direction and the chordwise direction, the generation of the inner shape curved surface of the wing wall plate is carried out in the selection step three, and the specific steps are as follows:
the method comprises the following steps: establishing a thickness line at the boundary along the direction of the appearance normal for each linearly-changed curved surface block between the two stringers, establishing an inner shape surface boundary line and a guide line by taking the thickness line as the boundary and the outer shape surface as the guide, and establishing an inner shape surface by taking the inner shape surface boundary line and the guide line as the reference; according to the method, an inner curved surface of each linear change area is created, a complete curved surface from the wing root to the wing tip between two stringers is spliced by the inner curved surface blocks, and each two inner curved surface blocks are continuous in a first order at the boundary;
step two: establishing a thickness line at each rib position between the two stringers along the direction of the appearance normal, establishing an inner profile surface section line and a guide line by taking the thickness line as a boundary and taking an outer profile curved surface as a guide, and establishing a complete curved surface between the two stringers from the wing root to the wing tip by taking the section line of the inner profile surface and the guide line as a reference, wherein the curved surface is smooth and continuous in a second order at each rib position;
step three: establishing a thickness line at the intersection point of each stringer and each rib along the direction of the profile normal, and establishing a guide line of an inner profile at each stringer by taking the thickness line as a boundary and taking an outer profile curved surface as a guide; at each rib position, a section line of an inner surface is created by taking the thickness line as a boundary and taking the outer curved surface as a guide; then, a complete inner-shaped curved surface is created by taking the section lines and the guide lines of the inner-shaped surface as reference, and the curved surface is smooth and continuous in the second order at each control point.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109214032B (en) * | 2017-12-07 | 2019-06-21 | 中国航空制造技术研究院 | A kind of adaptive machining method of hollow blade |
| CN112861244B (en) * | 2019-11-28 | 2024-04-05 | 中国商用飞机有限责任公司 | Integral wallboard unfolding method based on layering thickness |
| CN112580150B (en) * | 2020-12-24 | 2024-02-27 | 中航贵州飞机有限责任公司 | Modification fitting method of aircraft part process model |
| CN114833528B (en) * | 2022-03-31 | 2023-05-23 | 山西汾西重工有限责任公司 | Forming method and device for totally-enclosed cavity type special-shaped curved wing |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102902851A (en) * | 2012-09-21 | 2013-01-30 | 西安飞机工业（集团）有限责任公司 | Unfolding modeling method for airplane integral panels based on computer-graphics aided three-dimensional interactive application (CATIA) |
| CN104750892A (en) * | 2013-12-31 | 2015-07-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Three-dimensional modeling method for thickness-variable curved-surface part inner shape surface |
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| GB0712552D0 (en) * | 2007-06-29 | 2007-08-08 | Airbus Uk Ltd | Elongate composite structural members and improvements therein |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102902851A (en) * | 2012-09-21 | 2013-01-30 | 西安飞机工业（集团）有限责任公司 | Unfolding modeling method for airplane integral panels based on computer-graphics aided three-dimensional interactive application (CATIA) |
| CN104750892A (en) * | 2013-12-31 | 2015-07-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Three-dimensional modeling method for thickness-variable curved-surface part inner shape surface |
Non-Patent Citations (3)
| Title |
|---|
| 基于CATIA的飞机展开壁板数字化模型的建立;甘忠等;《锻压技术》;20060630;第31卷(第6期);第110-114页 * |
| 逆向工程和二次开发技术在机翼壁板展开及建模中的应用;阳波等;《智能制造》;20140930(第9期);第49-53页 * |
| 飞机壁板展开件CATIA建模技巧研究;曹蔚等;《机械》;20101130;第37卷(第11期);第46-49页 * |
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