CN114638049A - Modeling method, device and equipment for aircraft structure frame process boss and storage medium - Google Patents
Modeling method, device and equipment for aircraft structure frame process boss and storage medium Download PDFInfo
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Abstract
The application discloses a modeling method, a device, equipment and a storage medium for a craft boss of an airplane structure frame, wherein a spline curve analytic expression is obtained through craft boss parameters; establishing a local coordinate system based on the process boss parameters and the spline curve analytic expression; converting the local coordinate system into an airplane coordinate system, and acquiring coordinates of the corner points of the process bosses in the airplane coordinate system; acquiring interface information of a process boss-product model based on the process boss parameters; and modeling the process boss based on the coordinates and the interface information. The method solves the problems that in the prior art, the determination of the shape and position relationship between the process boss and the structural frame part and the geometric dimension of the process boss and the structural frame part mainly depend on the extraction of the profile characteristics of the product part to manually complete the model construction work, and the problems of more repetitive labor and great process characteristic extraction difference to cause difficult maintenance and change exist.
Description
Technical Field
The application relates to the field of modeling of aircraft structure frames, in particular to a method, a device, equipment and a storage medium for modeling an aircraft structure frame process boss.
Background
The aircraft body structure mainly comprises a structure frame, a beam, a stringer, a skin and the like, wherein parts of the structure frame are used for bearing concentrated loads in a frame plane and transmitting the concentrated loads to the skin of an aircraft body in a distributed shear flow mode. The bearing load is large, and the bearing component is an important bearing component of an airplane structure.
According to the stress form, the structural frame can be divided into an annular rigid frame type structural frame, a web plate type structural frame and a framework type structural frame, and according to the structural form, the structural frame can be divided into an integral frame, a combined frame and a mixed frame.
The structural frame used on the current airplane mainly takes a web plate type integral frame as a main part. The structure has good strength, and can be integrated with various structures, such as intersection holes, joints and the like.
The aircraft structure frame generally needs to be fixed on a tool when being processed, a process boss is generally required to be arranged on the periphery of the structure frame, and the structure frame is fixed on the tool through a bolt, so that the structure frame is not moved when being processed. At present, model construction work of a process boss and a structural frame part is mainly completed manually, and the problems of more repetitive labor and difficulty in maintenance and modification due to large process feature extraction difference exist.
Therefore, a modeling method, a device, equipment and a storage medium for the aircraft structural frame process boss are needed to solve the problems.
Disclosure of Invention
The application mainly aims to provide a modeling method, a modeling device, modeling equipment and a storage medium for a process boss of an aircraft structure frame, and aims to solve the technical problems that in the prior art, the determination of the form and position relationship and the self geometric dimension of the process boss and the structural frame part mainly depends on the extraction of profile features of product parts to manually complete model construction work, so that the repeated labor is more, and the extraction difference of the process features is large, so that the maintenance and the change are difficult.
In order to achieve the above object, the present application provides a method for modeling an aircraft structure frame process boss, which includes the following steps:
acquiring a spline curve analytic expression based on the process boss parameters;
establishing a local coordinate system based on the process boss parameters and the spline curve analytic expression;
converting the local coordinate system into an airplane coordinate system, and acquiring coordinates of the corner points of the process bosses in the airplane coordinate system;
acquiring interface information of a process boss-product model based on the process boss parameters;
and modeling the process boss based on the coordinates and the interface information.
Optionally, the process boss parameters include: the coordinates of the boundary points of the part and the process boss, the profile surface of the part and the shape parameter vector of the process boss.
Optionally, the step of obtaining a spline curve analytic expression based on the process convex parameters includes:
acquiring the contour surface point positions of the neighborhood of the boundary points based on the process boss parameters;
and acquiring a spline curve analytic expression based on the contour surface point position of the boundary point neighborhood and the process boss parameter.
Optionally, the step of converting the local coordinate system into an airplane coordinate system and obtaining coordinates of corner points of the process boss in the airplane coordinate system includes:
and converting the local coordinate system into an airplane coordinate system, and acquiring the coordinates of the corner points of the process bosses positioned on the inner side of the contour surface of the part under the airplane coordinate system.
Optionally, the step of obtaining interface information of the process boss-product model based on the process boss parameter includes:
drawing a sketch of the process boss based on the process boss parameters;
drawing the sketch of the process boss to obtain a model entity;
and based on the model entity, segmenting the model entity to obtain the interface information of the process boss-product model.
Optionally, the step of segmenting the model entity based on the model entity to obtain interface information of the process boss-product model includes:
based on the model entity, carrying out segmentation Boolean operation on the model entity to obtain a segmentation direction;
and based on the segmentation direction, segmenting the model entity to obtain the interface information of the process boss-product model.
Optionally, before the step of obtaining the spline curve analytic expression based on the process convex parameters, the method further includes:
and receiving the technological boss parameters input by a user.
In addition, in order to achieve the above object, the present application further provides a modeling apparatus for an aircraft structural frame process boss, where the modeling apparatus for the aircraft structural frame process boss includes: the input module is used for inputting process boss parameters;
the acquisition module is used for acquiring the coordinates of the process boss corner points in the airplane coordinate system and the interface information of the process boss-product model based on the process boss parameters;
and the generating module is used for generating a model of the process boss based on the coordinates of the process boss corner points in the airplane coordinate system and the interface information of the process boss-product model.
In addition, to achieve the above object, the present application further provides an electronic device, which includes a memory and a processor, where the memory stores a computer program, and the processor executes the computer program to implement the method as described in any one of the above.
In addition, to achieve the above object, the present application further provides a computer-readable storage medium having a computer program stored thereon, wherein a processor executes the computer program to implement the method according to any one of the above aspects.
The modeling method, device, equipment and storage medium for the aircraft structure frame process boss provided by the embodiment of the application comprise the following steps:
acquiring a spline curve analytic expression based on the process boss parameters;
establishing a local coordinate system based on the process boss parameters and the spline curve analytic expression;
converting the local coordinate system into an airplane coordinate system, and acquiring coordinates of angular points of the process bosses in the airplane coordinate system;
acquiring interface information of a process boss-product model based on the process boss parameters;
and modeling the process boss based on the coordinates of the process boss corner points in the airplane coordinate system and the interface information of the process boss-product model.
The method can automatically acquire the spline analytic expression according to the parameters of the process boss, establish a local coordinate system by combining the spline analytic expression and the parameters of the process boss, convert the local coordinate system into an airplane coordinate system and acquire the coordinates of the corner point of the process boss under the airplane coordinate system. Meanwhile, interface information of the process boss-product model is obtained according to the process boss parameters. The process of obtaining the interface information and the process of obtaining the coordinate can be carried out simultaneously, and finally, a geometric model with corresponding characteristics is generated according to the coordinate and the interface information.
The method solves the problems that in the prior art, the determination of the form and position relationship between the process boss and the structural frame part and the geometric dimension of the process boss and the structural frame part is mainly realized by manually completing the model construction work by extracting the profile characteristics of the product part, and the problems of more repetitive labor and great process characteristic extraction difference cause difficulty in maintenance and modification.
Drawings
FIG. 1 is a schematic flow chart diagram illustrating an embodiment of a method for modeling an aircraft structural frame process boss according to the present application;
FIG. 2 is a schematic view of a refining process of the step of obtaining spline curve analytic expressions based on process convex parameters shown in FIG. 1;
fig. 3 is a schematic view of a detailed flow of the step of converting the local coordinate system into an aircraft coordinate system and acquiring coordinates of corner points of the process boss in the aircraft coordinate system in fig. 1;
FIG. 4 is a schematic flow chart illustrating a detailed process of the step of obtaining process boss-product model interface information based on the process boss parameters shown in FIG. 1;
FIG. 5 is a functional block diagram illustrating modeling of a process boss of an aircraft structural frame according to an embodiment of the present disclosure;
fig. 6 is a schematic diagram of process boss parameters of a process boss of an aircraft structural frame according to an embodiment of the present application;
FIG. 7 is a schematic diagram of a local coordinate system of a craft boss of an aircraft structural frame according to an embodiment of the present application;
fig. 8 is a schematic diagram of interface information of a process boss-product model of a process boss of an aircraft structural frame according to an embodiment of the present application;
FIG. 9 is a parameterized rapid modeling human-computer interaction interface of an aircraft structural frame process boss provided in an embodiment of the present application;
the implementation, functional features and advantages of the object of the present application will be further explained with reference to the embodiments, and with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The main solution of the embodiment of the application is as follows:
because the airplane body structure in the prior art mainly comprises a structure frame, a beam, a stringer, a skin and the like, parts of the structure frame are used for bearing concentrated loads in a frame plane and transmitting the concentrated loads to the fuselage skin in a distributed shear flow mode. The bearing load is large, and the bearing component is an important bearing component of an airplane structure.
According to the stress form, the structural frame can be divided into an annular rigid frame type structural frame, a web plate type structural frame and a framework type structural frame, and according to the structural form, the structural frame can be divided into an integral frame, a combined frame and a mixed frame.
The structural frame used on the current airplane mainly takes a web plate type integral frame as a main part. The structure has good strength, and can be integrated with various structures, such as intersection holes, joints and the like.
The aircraft structure frame generally needs to be fixed on a tool when being processed, a process boss is generally required to be arranged on the periphery of the structure frame, and the structure frame is fixed on the tool through a bolt, so that the structure frame is not moved when being processed. A typical process panel distribution is shown in figure 1. In the face of a large number of structural frame parts with complex form and position relations, a large amount of process boss modeling work needs to be repeated by process personnel. At present, the shape and position relationship between a process boss and a structural frame part and the geometric dimension of the process boss are determined mainly by manually completing model construction work by extracting profile features of product parts, the problems of more repetitive labor, large process feature extraction difference, difficulty in maintenance and change and the like exist, quality and production requirements are difficult to meet in the aspects of economy and maintainability, and how to quickly, efficiently and stably realize process boss modeling needs to be solved urgently. The application provides a solution, so that the modeling process of the aircraft structure frame process boss becomes simpler and more convenient.
Referring to fig. 1, an embodiment of a method, an apparatus, a device and a storage medium for modeling an aircraft structural frame process boss according to the present application provides a method for modeling an aircraft structural frame process boss, where the method for modeling an aircraft structural frame process boss includes:
and step S10, acquiring a spline curve analytic expression based on the process boss parameters. The above-mentioned process boss parameters are basic conditions for modeling, and as shown in fig. 6, the process boss parameters mainly include: the coordinates of the boundary points of the part and the process boss, the profile surface of the part and the shape parameter vector of the process boss.
In mathematical science numerical analysis, a spline is a special function defined by polynomial segments. Spline interpolation is generally better than polynomial interpolation in the interpolation problem. Interpolation with splines of low order can produce similar effects to those of polynomial interpolation of high order and can avoid numerical instability, known as the longge phenomenon. And spline interpolation of low order also has the important property of "preserving convexity". In computer aided design and computer graphics in computer science, splines generally refer to piecewise defined polynomial parametric curves. The spline is a common representation method for curves in these fields because the spline has simple structure, convenient use and accurate fitting, and can approximate complex shapes in curve fitting and interactive curve design.
And step S20, establishing a local coordinate system based on the process boss parameters and the spline curve analytic expression. In geometry, a coordinate system is a system that uses one or more numbers or coordinates to uniquely determine the position of points or other geometric elements on a manifold (e.g., euclidean space). The order of the coordinates is important, sometimes identified by their position in the ordered tuple, sometimes identified by letters, as in the "x-coordinate". In elementary mathematics, coordinates are considered real numbers, but may also be complex numbers or elements of a more abstract system, such as commutative rings. The use of a coordinate system translates geometric problems into numerical problems and vice versa; this is the basis for analytic geometry and also for modeling.
And step S30, converting the local coordinate system into an airplane coordinate system, and acquiring coordinates of the corner points of the process bosses in the airplane coordinate system. To describe the state of motion of the aircraft, a suitable coordinate system must be selected. For example, the position of the aircraft relative to the ground, a ground coordinate system must be used; the rotation of the airplane is represented by a body coordinate system; the orbital motion of the aircraft can be expressed in terms of a velocity coordinate system. The coordinate axes defined below are all three-dimensional orthogonal axes and obey the right-hand rule, such as the ground inertia coordinate system, the body coordinate system, the air flow coordinate system, etc., and all of the coordinate systems point forward with the X-axis pointing to the right, with the Y-axis pointing to the right, and with the Z-axis pointing downward.
And step S40, acquiring interface information of the process boss-product model based on the process boss parameters. As shown in fig. 8, the interface information described above is also the basis for modeling.
And step S50, modeling the process boss based on the coordinates and the interface information.
In this embodiment, the method may automatically generate the geometric model of the corresponding feature according to the parameters of the process boss. The method solves the problems that in the prior art, the determination of the form and position relationship between the process boss and the structural frame part and the geometric dimension of the process boss and the structural frame part is mainly realized by manually completing the model construction work by extracting the profile characteristics of the product part, and the problems of more repetitive labor and great process characteristic extraction difference cause difficulty in maintenance and modification.
As an optional implementation manner, referring to fig. 2, in the modeling method for the aircraft structural frame process convex platform, the step of obtaining the spline curve analytic expression based on the process convex platform parameter includes:
and step S11, acquiring the contour surface point position of the boundary point neighborhood based on the process boss parameter.
By the boundary point coordinate P of the part and the process boss0(x0,y0,z0) And profile surface sigma: f (x, y, z) is 0 and the shape parameter vector S is (l)0,l1,l2,w1,w2,d1,d2,h1,h2) As the initial parameters of the process boss. Wherein l0From the bolt hole for clamping to the boundary point P0A distance of l1And l2Is a process boss and a boundary point P0Distance of (d), w1And w2Width of the technological boss, d1And d2Respectively the diameter of the bolt countersunk hole and the diameter of the hole corresponding to the screw section, h1And h2Is the thickness of the process boss. The accuracy of subsequent modeling can be improved by using the contour surface point positions of the boundary point neighborhood.
And step S12, acquiring a spline curve analytic expression based on the contour surface point position of the boundary point neighborhood and the process boss parameter. The spline curve analytic expression obtained by using the contour surface point positions of the boundary point neighborhood is more fit with the actual situation of the process boss, and the error is favorably reduced.
Selecting boundary point U (P)0) Neighborhood, the neighborhood range being w1×h1Reading points on the contour surfaceAnd (4) coordinates. Meanwhile, since the airplane framing main plane is generally in the STA (i.e. xoz plane) direction, discrete points (x) are needed1,z1)，(x2,z2),…,(xn,zn) Constructing a spline curve analytic expression, for which the lagrange interpolation is used to pair sigma at P0The analytical formula (iv) is defined as follows:
wherein,
is an interpolated basis function.
Therefore, according to the above formula, the contour surface Σ numerical analysis formula F (x, y, z) can be obtained as 0:
as an optional implementation manner, referring to fig. 3, in the modeling method for the craft boss of the aircraft structural frame according to the present application, the step of converting the local coordinate system into the aircraft coordinate system and acquiring coordinates of an angular point of the craft boss under the aircraft coordinate system includes:
and converting the local coordinate system into an airplane coordinate system, and acquiring the coordinates of the corner points of the process bosses positioned on the inner side of the contour surface of the part under the airplane coordinate system. It can be understood that, in order to save the procedure steps, the position relationship between the process boss and the contour surface of the part needs to be judged before the coordinates of the corner point of the process boss in the airplane coordinate system are obtained. If the process boss is positioned on the outer side of the profile surface of the part, the coordinates of the angular point of the process boss under an airplane coordinate system do not need to be acquired. By the steps, invalid operation can be saved, and efficiency is improved.
In the process of establishing a local coordinate system, in order to facilitate parameter calculation, an origin is taken: boundary point P0(x0,y0,z0)。
The x axis is as follows: contour curved surface sigma at P0Normal to Fx(x0,y0,z0)Fy(x0,y0,z0)Fz(x0,y0,z0)。
And a y axis: contour curved surface sigma at P0Tangent line F ofx(x0,y0,z0)(x-x0)+Fy(x0,y0,z0)(y-y0)＝0。
And a z-axis: the direction is determined according to a standard cartesian coordinate system.
Wherein, in order to judge whether the position of the process boss is outside or inside Σ, Σ is shifted by a certain distance δ in the positive direction of the normal line thereof to obtain Σ1The discrimination method is shown in table 1.
TABLE 1 relative position discrimination of process boss-part
| Σ1Whether it intersects with the part model | Relative position of process boss-part | Logical return value LΣ |
| Is that | Inside the contour curved |
1 |
| Whether or not | Outside the contour curved |
0 |
According to the creation of the origin and the coordinate axis and the judgment process of the relative position of the process boss and the part, the local coordinate system shown in the figure 7 can be established.
In the local coordinate system, the coordinates of each point are shown in table 2.
TABLE 2 Point location coordinates
Since table 1 obtains the local position coordinates of each corner point, in order to convert the coordinates into coordinates in the airplane coordinate system, the coordinate conversion relationship needs to be determined:
firstly, in order to make the local coordinate and the airplane coordinate consistent in direction, the local coordinate system rotates around an x axis, a y axis and a z axis respectively, and the rotation matrixes of three dimensions are R respectivelyx,Ry,Rz：
The rotational transformation of the local coordinates into the aircraft coordinates is represented as
Then, in order to make the local coordinate and the airplane coordinate coincide, the local coordinate system is translated along the x-axis, the y-axis and the z-axis by a distance tx,ty,tzIn the method proposed by the present invention, P is selected0Is a local origin of coordinates, so tx＝x0，tx＝y0，tz＝z0。
At this time, a point in the local coordinate system is checked
Which corresponds to aircraft coordinates of
The coordinate transformation relationship of the two can be expressed as follows:
to this end, all the corner points P on the process boss0～P9Can be determined in the aircraft coordinate system.
As an optional implementation manner, referring to fig. 4, in the modeling method of the aircraft structural frame process boss, the step of obtaining interface information of the process boss-product model based on the process boss parameter includes:
step S41, drawing a sketch of the process boss based on the process boss parameter;
step S42, stretching the sketch of the process boss to obtain a model entity;
and step S43, based on the model entity, segmenting the model entity to obtain the interface information of the process boss-product model.
As an optional implementation manner, referring to fig. 5, in the modeling method for an aircraft structural frame process boss according to the present application, the step of segmenting the model entity based on the model entity to obtain interface information of the process boss-product model includes:
step S431, based on the model entity, carrying out segmentation Boolean operation on the model entity to obtain a segmentation direction; boolean operations, also known as logical operations, are logical mathematical calculations that deal with the relationship between two values. The boolean operation obtains a new object form by performing a union, difference, intersection operation on more than two objects. The system provides 3 Boolean operation modes: union, intersection and difference. The difference set comprises A-B and B-A. The object can modify the two operation objects at any time after Boolean operation, the Boolean operation mode and effect can be edited and modified, and the Boolean operation modification process can be recorded as animation to show a magic cutting effect.
And S432, based on the dividing direction, dividing the model entity to obtain interface information of the process boss-product model.
According to P0～P9Drawing the sketch of the process boss and putting the sketch along P0Stretching and transforming the section direction to obtain a corresponding model entity M0. Considering M0Intersect with sigma, while the process boss is only M0Need to use sigma-pair M0Performing segmentation Boolean operation, and analyzing the relative position of boss and part according to the process shown in Table 1 to determine whether split is L∑And the split side is the positive normal direction of the sigma, namely the dividing direction, and finally the interface information of the process boss-product model is obtained.
And finally, according to the position of the angular point of the process boss in the plane coordinate system and the interface information of the process boss and the part, the CATIA can be driven by a secondary development program to complete the process boss, parameterization and high efficiency are realized in the whole process, and the problems that in the prior art, the determination of the form and position relationship between the process boss and the structural frame part and the geometric dimension of the process boss are mainly realized by manually completing model construction by extracting the profile characteristics of the product part, the repeated labor is more, and the process characteristic extraction difference is large, so that the maintenance and the change are difficult are solved.
As an optional implementation manner, in the modeling method for the aircraft structural frame process convex platform, before the step of obtaining the spline curve analytic expression based on the process convex platform parameters, the method includes:
and receiving the technological boss parameters input by a user.
Referring to fig. 9, fig. 9 is a parameterized rapid modeling human-computer interaction interface, and artificial input of process boss parameters can improve modeling efficiency, and meanwhile, each parameter in the modeling process becomes visible, so that various midway operations are simplified.
Furthermore, in an embodiment, there is also provided a production device comprising a processor, a memory and a computer program stored in the memory, which computer program, when executed by the processor, implements the steps of the method in the preceding embodiments.
Furthermore, in an embodiment, the present application further provides a computer storage medium having a computer program stored thereon, where the computer program is executed by a processor to implement the steps of the method in the foregoing embodiments.
In some embodiments, the computer-readable storage medium may be memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash, magnetic surface memory, optical disk, or CD-ROM; or may be various devices including one or any combination of the above memories. The computer may be a variety of computing devices including intelligent terminals and servers.
In some embodiments, executable instructions may be written in any form of programming language (including compiled or interpreted languages), in the form of programs, software modules, scripts or code, and may be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.
By way of example, executable instructions may, but need not, correspond to files in a file system, and may be stored in a portion of a file that holds other programs or data, such as in one or more scripts in a hypertext Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code).
By way of example, executable instructions may be deployed to be executed on one computing device or on multiple computing devices at one site or distributed across multiple sites and interconnected by a communication network.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or system that comprises the element.
The above-mentioned serial numbers of the embodiments of the present application are merely for description and do not represent the merits of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which is stored in a storage medium (e.g., a rom/ram, a magnetic disk, an optical disk) and includes instructions for enabling a multimedia terminal (e.g., a mobile phone, a computer, a television receiver, or a network device) to execute the method according to the embodiments of the present application.
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all the equivalent structures or equivalent processes that can be directly or indirectly applied to other related technical fields by using the contents of the specification and the drawings of the present application are also included in the scope of the present application.
Claims (10)
1. A modeling method for an aircraft structure frame process boss is characterized by comprising the following steps:
acquiring a spline curve analytic expression based on the process boss parameters;
establishing a local coordinate system based on the process boss parameters and the spline curve analytic expression;
converting the local coordinate system into an airplane coordinate system, and acquiring coordinates of the angular point of the process boss under the airplane coordinate system;
acquiring interface information of a process boss-product model based on the process boss parameters;
and modeling the process boss based on the coordinates and the interface information.
2. The method of modeling an aircraft structural frame process kit as defined in claim 1, wherein the process kit parameters include: the coordinates of the boundary points of the part and the process boss, the profile surface of the part and the shape parameter vector of the process boss.
3. The method of modeling an aircraft structural frame process kit as defined in claim 2, wherein the step of obtaining a spline curve analytical expression based on the process kit parameters comprises:
acquiring the contour surface point positions of the neighborhood of the boundary points based on the process boss parameters;
and acquiring a spline curve analytic expression based on the contour surface point position of the boundary point neighborhood and the process boss parameter.
4. The modeling method of an aircraft structural frame process boss according to claim 2, wherein the step of converting the local coordinate system into an aircraft coordinate system and obtaining coordinates of corner points of the process boss under the aircraft coordinate system comprises:
and converting the local coordinate system into an airplane coordinate system, and acquiring the coordinates of the corner points of the process bosses positioned on the inner side of the contour surface of the part under the airplane coordinate system.
5. The method for modeling an aircraft structural frame process kit as defined in claim 1, wherein said step of obtaining process kit-product model interface information based on said process kit parameters comprises:
drawing a sketch of the process boss based on the process boss parameters;
drawing the sketch of the process boss to obtain a model entity;
and based on the model entity, segmenting the model entity to obtain the interface information of the process boss-product model.
6. The modeling method of an aircraft structural frame process boss according to claim 5, wherein the step of segmenting the model entity based on the model entity to obtain process boss-product model interface information includes:
based on the model entity, carrying out segmentation Boolean operation on the model entity to obtain a segmentation direction;
and based on the segmentation direction, segmenting the model entity to obtain the interface information of the process boss-product model.
7. The method for modeling an aircraft structural frame process kit as defined in claim 1, wherein prior to the step of obtaining a spline curve analytical formula based on process kit parameters, further comprising:
and receiving the technological boss parameters input by a user.
8. The utility model provides a modeling device of aircraft structure frame technology boss which characterized in that includes:
the input module is used for inputting process boss parameters;
the acquisition module is used for acquiring the coordinates of the process boss corner points in the airplane coordinate system and the interface information of the process boss-product model based on the process boss parameters;
and the generating module is used for generating a model of the process boss based on the coordinates of the process boss corner points in the airplane coordinate system and the interface information of the process boss-product model.
9. An electronic device, characterized in that the electronic device comprises a memory in which a computer program is stored and a processor, which executes the computer program, implementing the method according to any of claims 1-7.
10. A computer-readable storage medium, having a computer program stored thereon, which, when executed by a processor, performs the method of any one of claims 1-7.
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| 田富君;田锡天;耿俊浩;张振明;: "基于模型定义的工艺信息建模及应用", 计算机集成制造系统, no. 05, 15 May 2012 (2012-05-15), pages 19 - 25 * |
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