CN102436217A - Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure - Google Patents

Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure Download PDF

Info

Publication number
CN102436217A
CN102436217A CN2011103179734A CN201110317973A CN102436217A CN 102436217 A CN102436217 A CN 102436217A CN 2011103179734 A CN2011103179734 A CN 2011103179734A CN 201110317973 A CN201110317973 A CN 201110317973A CN 102436217 A CN102436217 A CN 102436217A
Authority
CN
China
Prior art keywords
edge
point
web
join
list
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN2011103179734A
Other languages
Chinese (zh)
Other versions
CN102436217B (en
Inventor
李迎光
刘旭
王伟
刘长青
李海
张石磊
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Maixinlin Aviation Technology Co ltd
Original Assignee
Nanjing University of Aeronautics and Astronautics
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN 201110317973 priority Critical patent/CN102436217B/en
Publication of CN102436217A publication Critical patent/CN102436217A/en
Application granted granted Critical
Publication of CN102436217B publication Critical patent/CN102436217B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Landscapes

  • Image Processing (AREA)

Abstract

本发明公开了一种飞机结构件槽特征腹板加工驱动几何自动重构方法,该方法首先结合槽特征的所有侧面、下陷面和转角面,计算出其边界;结合腹板面及其外环底角面,并计算其边界,将以上两个边界结合为一整体,并剔除不满足要求的边。在草图环境下,将筛选后的边向腹板面投影,求得投影后边与边的交点,并利用交点打断相交的边,基于投影和打断后的所有点和边,构造含有边、点以及边与点信息的属性边点图;然后计算出属性边点图中所有最小包围轮廓;最后从所有最小包围轮廓中得到有效的最小包围轮廓作为腹板加工驱动几何。本发明有效地解决了腹板驱动几何难以自动提取的问题,提高了数控工艺编程中腹板自动编程的质量和效率。

Figure 201110317973

The invention discloses a method for automatically reconfiguring the driving geometry of groove feature webs of aircraft structural parts. The method firstly combines all side surfaces, sunken surfaces and corner surfaces of the groove features to calculate their boundaries; combines the web surface and its outer ring The bottom corner face, and its boundary is calculated, the above two boundaries are combined into a whole, and the edges that do not meet the requirements are eliminated. In the sketch environment, project the screened edge to the web surface, obtain the intersection point between the projected edge and the edge, and use the intersection point to break the intersecting edge. Based on all the points and edges after projection and breaking, construct the edge, The attribute edge point graph of points and edge and point information; then calculate all the minimum enclosing contours in the attribute edge point graph; finally get the effective minimum enclosing contour from all the minimum enclosing contours as the driving geometry of web processing. The invention effectively solves the problem that the web driving geometry is difficult to automatically extract, and improves the quality and efficiency of web automatic programming in numerical control process programming.

Figure 201110317973

Description

飞机结构件槽特征腹板加工驱动几何重构方法Machining-driven geometry reconstruction method for slot feature webs of aircraft structural parts

技术领域 technical field

本发明涉及一种腹板加工驱动几何重构方法,尤其涉及一种飞机结构件槽特征腹板加工驱动几何重构方法,属于CAD(计算机辅助设计)/CAPP(计算机辅助工艺过程设计)/CAM(计算机辅助制造)技术领域。  The invention relates to a method for geometric reconstruction of web processing drive, in particular to a method for geometric reconstruction of web processing drive geometry of aircraft structural part grooves, belonging to CAD (Computer Aided Design)/CAPP (Computer Aided Process Design)/CAM (Computer Aided Manufacturing) technology field. the

背景技术 Background technique

飞机结构件结构复杂,加工特征多,包含大量自由曲面、相交特征和特殊加工区域,加工难度大。国内各大型航空企业投入数百亿巨额资金购买大量先进的数控机床,但设备有效利用率低,其主要原因在于数控编程效率低、质量不稳定。飞机结构件数控编程过程中需人工捡取大量几何、设置大量参数和创建大量辅助几何。随着整体件、薄壁件及特种材料件的增多,数控编程工作量大幅度增加,飞机结构件的数控编程日益成为影响飞机研制周期的重要瓶颈之一。  The structure of aircraft structural parts is complex, with many processing features, including a large number of free-form surfaces, intersecting features and special processing areas, making processing difficult. Large domestic aviation companies have invested tens of billions of dollars to purchase a large number of advanced CNC machine tools, but the effective utilization rate of the equipment is low. The main reason is the low efficiency and unstable quality of CNC programming. During the NC programming of aircraft structural parts, it is necessary to manually pick up a large number of geometries, set a large number of parameters and create a large number of auxiliary geometries. With the increase of integral parts, thin-walled parts and special material parts, the workload of NC programming has increased significantly, and the NC programming of aircraft structural parts has increasingly become one of the important bottlenecks affecting the aircraft development cycle. the

驱动信息的自动获取过程称为加工特征重构。驱动几何自动重构是加工特征重构中的重点和难点。驱动几何隐含在加工特征的几何信息中,需经处理转换为刀轨生成算法可直接使用的数据形式。  The automatic acquisition process of driving information is called machining feature reconstruction. The automatic reconstruction of driving geometry is the key and difficult point in the reconstruction of machining features. The driving geometry is implicit in the geometric information of the machining features, which needs to be processed and converted into a data form that can be directly used by the tool path generation algorithm. the

在B-rep(边界表示法)表示的CAD模型中,面是用点、边、环来组织其拓扑结构的。.面的边界由环组成,环分为内环和外环,外环有且仅有1个,内环可以有多个。外环构成面的外轮廓,内环构成孔轮廓或岛屿轮廓。内、外环是腹板加工刀轨生成算法的直接驱动几何。  In the CAD model represented by B-rep (Boundary Representation), the topology of the surface is organized by points, edges, and rings. .The boundary of a surface is composed of rings. The rings are divided into inner rings and outer rings. There is only one outer ring, and there can be multiple inner rings. The outer ring forms the outer contour of the surface, and the inner ring forms the contour of the hole or island. The inner and outer rings are the direct drive geometry for the web machining tool path generation algorithm. the

飞机结构件槽腔形状复杂、封闭性不一,槽腔侧壁包含大量自由曲面、开闭角并存,腹板面自身外环不能直接作为等距线的偏置依据。因此,必须对外环进行修正,包含大量的曲线裁剪拼接计算,以保证刀具在切削过程中既不与侧面发生干涉,也不会产生切削残留。目前的方法都是在三维环境下进行腹板驱动几何的选取与裁剪,工作量大,且正确性难以保证,尤其是在自动计算的过程中,难以生成有效的封闭驱动几何。  The shape of the cavity of aircraft structural parts is complex and the sealing is different. The side wall of the cavity contains a large number of free-form surfaces and the opening and closing angles coexist. The outer ring of the web surface itself cannot be directly used as the offset basis of the equidistance line. Therefore, the outer ring must be corrected, including a large number of curve cutting and splicing calculations, so as to ensure that the tool will neither interfere with the side surface nor produce cutting residue during the cutting process. The current method is to select and cut the driving geometry of the web in a 3D environment, which has a large workload and is difficult to guarantee the correctness, especially in the process of automatic calculation, it is difficult to generate an effective closed driving geometry. the

发明内容 Contents of the invention

本发明所要解决的技术问题在于克服现有CAD/CAM系统中结构件槽特征腹板加工驱 动几何计算方法的不足,提供一种飞机结构件槽特征腹板加工驱动几何自动重构的方法。  The technical problem to be solved by the present invention is to overcome the deficiencies of the existing CAD/CAM system in the structural part groove characteristic web processing driving geometry calculation method, and to provide a method for automatic reconstruction of the aircraft structural part groove characteristic web processing driving geometry. the

本发明的飞机结构件槽特征腹板加工驱动几何自动重构方法包括以下步骤:  The method for automatically reconfiguring the driving geometry of the groove feature web of the aircraft structural part of the present invention comprises the following steps:

步骤1、结合一个槽特征的所有侧面、下陷面和转角面,标记为JOIN.1;  Step 1. Combine all sides, sunken faces and corner faces of a groove feature, marked as JOIN.1;

步骤2、根据JOIN.1中所有面之间的邻接关系,计算出其边界,标记为:BOUNDARY.1;  Step 2. According to the adjacency relationship between all faces in JOIN.1, calculate its boundary, marked as: BOUNDARY.1;

步骤3、结合腹板面和腹板外环底角面,标记为:JOIN.2;  Step 3. Combine the web surface and the bottom corner surface of the outer ring of the web, marked as: JOIN.2;

步骤4、根据JOIN.2中所有面之间的邻接关系,得到其边界,标记为:BOUNDARY.2;  Step 4. According to the adjacency relationship between all faces in JOIN.2, get its boundary, marked as: BOUNDARY.2;

步骤5、结合BOUNDARY.1和BOUNDARY.2中的所有边为一整体,标记为:JOIN.3;  Step 5. Combine all edges in BOUNDARY.1 and BOUNDARY.2 into a whole, marked as: JOIN.3;

步骤6、筛选JOIN.3中的边,剔除不需要的边;  Step 6. Filter the edges in JOIN.3 and eliminate unnecessary edges;

步骤7、在草图环境下,将筛选后的JOIN.3中的边向腹板面投影,求得投影后边与边的交点,并利用交点打断相交的边,处理后的结果标记为SKETCH.1;  Step 7. In the sketch environment, project the edge in the filtered JOIN.3 to the web surface, obtain the intersection point between the projected edge and the edge, and use the intersection point to break the intersecting edge. The processed result is marked as SKETCH. 1;

步骤8、基于投影和打断后的所有点和边,构造含有边、点以及边与点信息的属性边点图;  Step 8. Based on all points and edges after projection and interruption, construct an attribute edge-point graph containing edge, point, and edge-to-point information;

步骤9、计算出属性边点图中所有最小包围轮廓;  Step 9, calculate all minimum enclosing contours in the attribute edge point graph;

步骤10、从所有最小包围轮廓得到有效的最小包围轮廓,即为最终的腹板轮廓加工驱动几何。  Step 10. Obtain an effective minimum enclosing contour from all the minimum enclosing contours, which is the driving geometry for the final web contour machining. the

所述步骤2的具体步骤是:①按照顺序逐个取出JOIN.1中的面;②提取该面的外环边界;③按照顺序逐个取出外环边界中的边;④判断该边是否属于JOIN.1中其它面的外环边,若是,则返回步骤③,否则,该边线属于JOIN.1的边界,将其列入BOUNDARY.1。  The specific steps of step 2 are: ① take out the faces in JOIN.1 one by one in order; ② extract the outer ring boundary of the face; ③ take out the edges in the outer ring boundary one by one in order; ④ judge whether the edge belongs to JOIN. For the outer ring edges of other faces in 1, if yes, return to step ③; otherwise, this edge belongs to the boundary of JOIN.1, and it is included in BOUNDARY.1. the

所述的筛选JOIN.3的边的方法是:①剔除JOIN.3中相同的边;②剔除垂直于腹板面的直边。  The method for screening the edges of JOIN.3 is: ① remove the same edges in JOIN.3; ② remove the straight edges perpendicular to the web surface. the

所述步骤7的具体步骤是:①将得到的三维边向腹板平面投影,得到平面直线、平面圆锥曲线或者平面样条曲线等投影曲线;②对于完全重合的曲线,只保留一条,对于部分重合的曲线,求出重合部分并且只保留一条;③然后求出曲线之间所有的交点,在每一个交点处将相应的曲线打断成两条曲线,最终得到一个网状的曲线列。  The specific steps of said step 7 are: 1. Project the obtained three-dimensional edge to the web plane to obtain projection curves such as plane straight lines, plane conic curves or plane spline curves; For the overlapped curves, find the overlapped part and keep only one; ③ Then find all the intersection points between the curves, break the corresponding curve into two curves at each intersection point, and finally get a network of curves. the

以上过程在CAD/CAM软件中的实现方法:基于腹板平面创建草图,将JOIN.3整体向草图投影,即可实现JOIN.3中的边线向腹板面投影,求交点,打断等操作;  The realization method of the above process in CAD/CAM software: create a sketch based on the web plane, and project JOIN.3 as a whole to the sketch, so that the edge lines in JOIN.3 can be projected to the web surface, intersecting points, interruption and other operations can be realized ;

所述步骤8的具体步骤是:①定义点类MyVertex,成员变量包括点的数学表示、点的拓扑表示以及与点相连的拓扑边列;②定义边类MyEdge,成员变量包括边的拓扑表示、边的特征表示、边的开闭口属性标识、起始点、终止点;③新建一个MyVertex类的列表,标记为:MYVERTEX_LIST,新建一个MyEdge类的列表,标记为:MYEDGE_LIST;④按照顺序逐个取出SKETCH.1中的边;⑤新建一个MyEdge类的对象,将当前边的属性填入对应的成员变量中,并且将该对象列入MYEDGE_LIST中;⑥取出当前边的起始点,标记为 STARTPOINT。判断STARTPOINT是否为MYVERTEX_LIST中的成员,若是,则跳至第⑦步,否则新建一个MyVertex类的对象,将STARTPOINT的属性填入对应的成员中并且将该对象列入MYVERTEX_LIST中;⑦取出当前边的终止点,标记为ENDPOINT。判断ENDPOINT是否为MYVERTEX_LIST中的成员,若不是则新建一个MyVertex类的对象,将ENDPOINT的属性填入对应的成员变量中,并且将该对象列入MYVERTEX_LIST中。  The concrete steps of described step 8 are: 1. define the point class MyVertex, member variables include the mathematical representation of the point, the topological representation of the point and the topological edge column connected with the point; 2. define the edge class MyEdge, the member variables include the topological representation of the edge, The feature representation of the edge, the opening and closing attribute identification of the edge, the starting point, and the ending point; ③ Create a list of the MyVertex class and mark it as: MYVERTEX_LIST, and create a list of the MyEdge class and mark it as: MYEDGE_LIST; ④ Take out the SKETCH one by one in order. 1 edge; ⑤ create a MyEdge class object, fill in the current edge attributes into the corresponding member variables, and list the object in MYEDGE_LIST; ⑥ take out the starting point of the current edge, and mark it as STARTPOINT. Determine whether STARTPOINT is a member of MYVERTEX_LIST, if so, skip to step ⑦, otherwise create a MyVertex object, fill in the attributes of STARTPOINT into the corresponding member and list the object in MYVERTEX_LIST; ⑦Take out the current edge End point, marked ENDPOINT. Determine whether ENDPOINT is a member of MYVERTEX_LIST, if not, create an object of MyVertex class, fill in the attributes of ENDPOINT into the corresponding member variable, and list the object in MYVERTEX_LIST. the

所述步骤9的具体步骤是:  The concrete steps of described step 9 are:

①在属性边点图中任取一段曲线li,取li的一个顶点Mi(x0,y0,z0)为当前结点,标记当前曲线与当前结点的组合,记为(li,Mi);  ①Choose a section of curve l i in the attribute edge-point graph, take a vertex M i (x 0 , y 0 , z 0 ) of l i as the current node, and mark the combination of the current curve and the current node, denoted as ( l i , M i );

②将组合(li,Mi)的点Mi作为曲线段的起点,假设曲线li在点Mi切矢为 

Figure DEST_PATH_GDA0000134382590000031
与当前结点Mi连接的其他线段的切矢 
Figure DEST_PATH_GDA0000134382590000032
② Take the point M i of the combination (l i , M i ) as the starting point of the curve segment, assuming that the tangent vector of the curve l i at point M i is
Figure DEST_PATH_GDA0000134382590000031
Tangent vectors of other line segments connected to the current node M i
Figure DEST_PATH_GDA0000134382590000032

③记腹板外法向为 

Figure DEST_PATH_GDA0000134382590000033
定义 
Figure DEST_PATH_GDA0000134382590000034
的旋转方向为 
Figure DEST_PATH_GDA0000134382590000035
那么 绕点Mi,以 
Figure DEST_PATH_GDA0000134382590000037
为起始方向旋转,在 
Figure DEST_PATH_GDA0000134382590000038
矢量中,与其重合的矢量相对应的第一条边即为当前最小包围轮廓线的下一条边,记为li1,取li1的另外一个顶点,记为Mi1,此时判断li1是否与li相同,如果不同则判断(li1,Mi1)是否已经标记,若没有标记,则将(li1,Mi1)赋值给(li,Mi)转入步骤②。  ③Record the outer normal direction of the web as
Figure DEST_PATH_GDA0000134382590000033
definition
Figure DEST_PATH_GDA0000134382590000034
The direction of rotation is
Figure DEST_PATH_GDA0000134382590000035
So Around the point M i , take
Figure DEST_PATH_GDA0000134382590000037
is the starting direction of rotation, at
Figure DEST_PATH_GDA0000134382590000038
In the vector, the first edge corresponding to the coincident vector is the next edge of the current minimum enclosing contour line, which is denoted as l i1 , and the other vertex of l i1 is denoted as M i1 , at this time, judge whether l i1 is Same as l i , if different, judge whether (l i1 , M i1 ) has been marked, if not, assign (l i1 , M i1 ) to (l i , M i ) and go to step ②.

④取li的另一个顶点为当前结点Mi′(x0′,y0′,z0′),判断(li,Mi′)是否已经标记,如果没有标记,则将(li,Mi′)赋值给(li,Mi)转入步骤②。  ④ Take another vertex of l i as the current node M i ′(x 0 ′, y 0 ′, z 0 ′), judge whether (l i , M i ′) has been marked, if not, set (l i , M i ′) assign value to (l i , M i ) and go to step ②.

⑤得到草图中所有的最小包围轮廓。  ⑤ Get all the minimum enclosing contours in the sketch. the

判断所述 

Figure DEST_PATH_GDA0000134382590000039
矢量中,与 
Figure DEST_PATH_GDA00001343825900000310
第一个相重合的矢量的具体步骤是:  Judgment said
Figure DEST_PATH_GDA0000134382590000039
in vector, with
Figure DEST_PATH_GDA00001343825900000310
The specific steps for the first coincident vector are:

①,以Mi为圆心,半径为1做圆。该圆与 

Figure DEST_PATH_GDA00001343825900000311
相交于点 
Figure DEST_PATH_GDA00001343825900000312
与 矢量相交于点  L n = M i + r → n . ①, Make a circle with M i as the center and a radius of 1. the circle with
Figure DEST_PATH_GDA00001343825900000311
intersect at point
Figure DEST_PATH_GDA00001343825900000312
and vector intersects at point L no = m i + r &Right Arrow; no .

②以L0为起点构造n个向量 V 1 → = L 1 - L 0 = r 1 → - r 0 → , V 2 → = L 2 - L 0 = r 2 → - r 0 → , . . . , V n → = L n - L 0 = r n → - r 0 → . ② Construct n vectors starting from L 0 V 1 &Right Arrow; = L 1 - L 0 = r 1 &Right Arrow; - r 0 &Right Arrow; , V 2 &Right Arrow; = L 2 - L 0 = r 2 &Right Arrow; - r 0 &Right Arrow; , . . . , V no &Right Arrow; = L no - L 0 = r no &Right Arrow; - r 0 &Right Arrow; .

③然后分别计算 

Figure DEST_PATH_GDA0000134382590000041
与 
Figure DEST_PATH_GDA0000134382590000042
向量之间的夹角,最小夹角对应的矢量即为与 第一个相重合的矢量。  ③ Then calculate separately
Figure DEST_PATH_GDA0000134382590000041
and
Figure DEST_PATH_GDA0000134382590000042
The angle between the vectors, the vector corresponding to the minimum angle is the The first coincident vector.

所述步骤10的具体步骤是:  The concrete steps of described step 10 are:

①得到的所有最小包围轮廓可以表示为:LOOP0,LOOP1,...,LOOPn;  ① All the minimum enclosing contours obtained can be expressed as: LOOP0, LOOP1, ..., LOOPn;

②排除面积最大的最小包围轮廓LOOPi(0≤i≤n),剩余的最小包围轮廓可以表示为:LOOP0,LOOP1,...LOOPi-1,LOOPi+1,...,LOOPn;  ②Exclude the minimum enclosing contour LOOPi (0≤i≤n) with the largest area, and the remaining minimum enclosing contours can be expressed as: LOOP0, LOOP1, ... LOOPi-1, LOOPi+1, ..., LOOPn;

③遍历剩余的最小包围轮廓,计算当前最小包围轮廓中心点,过中心点做垂直腹板面的直线,若该直线不与JOIN.1相交,则当前最小包围轮廓即为有效最小包围轮廓。  ③ Traverse the remaining minimum enclosing contours, calculate the center point of the current minimum enclosing contour, and make a straight line perpendicular to the web surface through the center point. If the straight line does not intersect JOIN.1, the current minimum enclosing contour is the effective minimum enclosing contour. the

本发明方法效率高,生成的腹板加工驱动几何质量高,计算过程中生成的辅助几何少,节省了存储空间,有效地解决了飞机结构件槽特征腹板加工驱动几何计算的繁琐、难以自动生成有效驱动几何的问题。  The method of the present invention has high efficiency, the generated web processing and driving geometry has high quality, and the auxiliary geometry generated in the calculation process is less, saving storage space, and effectively solving the cumbersome calculation of the characteristic web processing and driving geometry of aircraft structural parts, which is difficult to automate Generate problems that drive geometry efficiently. the

附图说明 Description of drawings

图1.本发明的飞机结构件槽特征腹板加工驱动几何生成方法流程图;  Fig. 1. flow chart of the method for generating the driving geometry of the groove feature web of the aircraft structural part of the present invention;

图2.结合面边界的算法流程图;  Figure 2. Algorithm flow chart for binding surface boundaries;

图3.网状的曲线列。其中,数字1-11表示曲线列的编号;LOOP1-LOOP6表示最小包围轮廓;  Figure 3. Curved columns of mesh. Among them, the number 1-11 represents the number of the curve column; LOOP1-LOOP6 represents the minimum enclosing contour;

图4.属性边点图类的定义;  Figure 4. Definition of attribute edge point graph class;

图5.属性边点图的构造流程图;  Figure 5. The construction flow chart of the attribute edge point graph;

图6.结点在线段上的切矢。其中Mi为当前曲线li的当前结点, 

Figure DEST_PATH_GDA0000134382590000044
为li在Mi处的单位切向量;  Figure 6. Tangent vectors of nodes on line segments. Where M i is the current node of the current curve l i ,
Figure DEST_PATH_GDA0000134382590000044
is the unit tangent vector of l i at M i ;

图7.矢量重合判断示意图。其中 

Figure DEST_PATH_GDA0000134382590000045
为当前曲线l0在当前结点Mi处的单位切向量, 
Figure DEST_PATH_GDA0000134382590000046
为与Mi相连的曲线ln在Mi处的单位切向量, 
Figure DEST_PATH_GDA0000134382590000047
为 
Figure DEST_PATH_GDA0000134382590000048
的旋转方向;  Figure 7. Schematic diagram of vector coincidence judgment. in
Figure DEST_PATH_GDA0000134382590000045
is the unit tangent vector of the current curve l 0 at the current node Mi ,
Figure DEST_PATH_GDA0000134382590000046
is the unit tangent vector of the curve l n connected to M i at M i ,
Figure DEST_PATH_GDA0000134382590000047
for
Figure DEST_PATH_GDA0000134382590000048
direction of rotation;

图8.实施例中使用的槽;  Fig. 8. Groove used in the embodiment;

图9.Join.1,表示槽特征的所有侧面、下陷面和转角面的结合;  Figure 9.Join.1, which represents the combination of all sides, sunken faces and corner faces of the groove feature;

图10.Join.2,表示槽特征的腹板面和底角面的结合;  Figure 10.Join.2, representing the combination of the web face and the bottom corner face of the groove feature;

图11.Join.3向腹板面投影后的草图,数字1-5表示草图中有交叉的部位;  Figure 11. The sketch after projection of Join.3 to the web surface, the numbers 1-5 indicate the intersection parts in the sketch;

图12.图11中“1”处的放大图;  Figure 12. The enlarged view at "1" in Figure 11;

图13.本发明的方法实现结果图,Guidel为有效最小包围轮廓,Bottom为腹板面;  Fig. 13. The result diagram of the realization of the method of the present invention, Guidel is the effective minimum enclosing contour, and Bottom is the web surface;

具体实施方式 Detailed ways

下面结合实施例和附图对本发明进一步说明。采用C++语言实现飞机结构件槽特征腹板加工驱动几何自动重构方法,采用的CAD/CAM软件平台为CATIA,开发平台为CATIA二次开发平台CAA,实施的具体步骤为:  The present invention will be further described below in conjunction with the embodiments and accompanying drawings. The C++ language is used to realize the automatic geometry reconstruction method driven by the groove feature web of aircraft structural parts. The CAD/CAM software platform used is CATIA, and the development platform is CAA, the secondary development platform of CATIA. The specific steps of implementation are as follows:

步骤1、执行“Join”命令,接合一个槽特征的所有侧面、下陷面和转角面,如图9所示,得到“Join.1”特征;  Step 1. Execute the "Join" command to join all the sides, sunken faces and corner faces of a groove feature, as shown in Figure 9, to get the "Join.1" feature;

步骤2、执行“Boundary”命令,计算出“Join.1”的边界,得到“Boundary.1”特征;  Step 2. Execute the "Boundary" command to calculate the boundary of "Join.1" and obtain the feature of "Boundary.1";

步骤3、执行“Join”命令,接合腹板面和腹板外环底角面,如图10所示,得到“Join.2”特征;  Step 3. Execute the "Join" command to join the web surface and the bottom corner surface of the outer ring of the web, as shown in Figure 10, to obtain the "Join.2" feature;

步骤4、执行“Boundary”命令,计算出“Join.2”的边界,得到“Boundary.2”特征;  Step 4. Execute the "Boundary" command to calculate the boundary of "Join.2" and obtain the feature of "Boundary.2";

步骤5、执行“Join”命令,将“Boundary.1”与“Boundary.2”结合为一整体,得到“Join.3”特征;  Step 5. Execute the "Join" command to combine "Boundary.1" and "Boundary.2" into a whole to get the "Join.3" feature;

步骤6、在草图环境下,将“Join.3”向腹板面投影,如图11所示,得到“Join.3向腹板面投影后的草图”特征,在CATIA中,投影草图后系统已经自动将所有相交曲线打断;  Step 6. In the sketch environment, project "Join.3" to the web surface, as shown in Figure 11, and get the feature of "Sketch after joining.3 projected to the web surface". In CATIA, after projecting the sketch, the system All intersecting curves have been automatically interrupted;

步骤7、构造含有边、点以及边与点信息的属性边点图。具体步骤是:①定义点类MyVertex,成员变量包括点的数学表示、点的拓扑表示以及与点相连的拓扑边列;②定义边类MyEdge,成员变量包括边的拓扑表示、边的特征表示、边的开闭口属性标识、起始点、终止点;③新建一个MyVertex类的列表,标记为:MYVERTEX_LIST,新建一个MyEdge类的列表,标记为:MYEDGE_LIST;④按照顺序逐个取出SKETCH.1中的边;⑤新建一MyEdge类的对象,将当前边的属性填入对应的成员变量中,并且将该对象列入MYEDGE_LIST中;⑥取出当前边的起始点,标记为STARTPOINT。判断STARTPOINT是否为MYVERTEX_LIST中的成员,若是,则跳至第⑦步,否则新建一MyVertex类的对象,将STARTPOINT的属性填入对应的成员中并且将该对象列入MYVERTEX_LIST中;⑦取出当前边的终止点,标记为ENDPOINT。判断ENDPOINT是否为MYVERTEX_LIST中的成员,若不是则新建一个MyVertex类的对象,将ENDPOINT的属性填入对应的成员变量中,并且将该对象列入MYVERTEX_LIST中。  Step 7. Construct an attribute edge-point graph containing edge, point, and edge-to-point information. The specific steps are: ①Define the point class MyVertex, and the member variables include the mathematical representation of the point, the topological representation of the point, and the topological edge columns connected to the point; ②Define the edge class MyEdge, and the member variables include the topological representation of the edge, the characteristic representation of the edge, Edge opening and closing attribute identification, starting point, and ending point; ③ Create a list of MyVertex class, marked as: MYVERTEX_LIST, create a new list of MyEdge class, marked as: MYEDGE_LIST; ④ Take out the edges in SKETCH.1 one by one in order; ⑤Create an object of MyEdge class, fill in the attributes of the current edge into the corresponding member variables, and list the object in MYEDGE_LIST; ⑥Take out the starting point of the current edge, and mark it as STARTPOINT. Determine whether STARTPOINT is a member of MYVERTEX_LIST, if so, skip to step ⑦, otherwise create a MyVertex class object, fill in the attributes of STARTPOINT into the corresponding member and list the object in MYVERTEX_LIST; ⑦Take out the current edge End point, marked ENDPOINT. Determine whether ENDPOINT is a member of MYVERTEX_LIST, if not, create an object of MyVertex class, fill in the attributes of ENDPOINT into the corresponding member variable, and list the object in MYVERTEX_LIST. the

步骤8、计算出属性边点图中所有最小包围轮廓。图11中“1”处的放大图如图12所示,“2”至“5”处与“1”处类似;  Step 8. Calculate all minimum enclosing contours in the attribute edge-point graph. The enlarged view of "1" in Figure 11 is shown in Figure 12, and "2" to "5" are similar to "1";

图12中的结点包括ABCDEFGHIJ,其中最小包围轮廓为ABCD与DGA等,得到最小 包围轮廓ABCD的步骤如下。  The nodes in Fig. 12 include ABCDEFGHIJ, wherein the minimum enclosing contours are ABCD and DGA, etc., and the steps to obtain the minimum enclosing contour ABCD are as follows. the

遍历属性边点图中的曲线,假设当前曲线为AD,取AD的一个顶点A为当前结点,标记当前曲线与当前结点的组合,记为(AD,D);  Traverse the curves in the attribute edge-point graph, assuming that the current curve is AD, take a vertex A of AD as the current node, mark the combination of the current curve and the current node, and record it as (AD, D);

在组合(AD,D)中,D为起始点,做曲线段DA、DG、DE和DC的切矢,并且单位化,分别记为 

Figure DEST_PATH_GDA0000134382590000061
In the combination (AD, D), D is the starting point, and the tangent vectors of the curve segments DA, DG, DE, and DC are made, and the units are denoted as
Figure DEST_PATH_GDA0000134382590000061

记腹板面的外法向为 

Figure DEST_PATH_GDA0000134382590000062
那么定义 
Figure DEST_PATH_GDA0000134382590000063
的旋转方向为 
Figure DEST_PATH_GDA0000134382590000064
绕点D,以 
Figure DEST_PATH_GDA0000134382590000065
为起始方向旋转,在 
Figure DEST_PATH_GDA0000134382590000066
矢量中,与其重合的矢量相对应的第一条边为DC,即为当前最小包围轮廓线的下一条边,此时判断DC是否与当前曲线AD相同,如果不同则判断(DC,C)是否已经标记,若没有标记,则将(DC,C)转入步骤②;  Denote the outward normal direction of the web surface as
Figure DEST_PATH_GDA0000134382590000062
then define
Figure DEST_PATH_GDA0000134382590000063
The direction of rotation is
Figure DEST_PATH_GDA0000134382590000064
Around point D, with
Figure DEST_PATH_GDA0000134382590000065
is the starting direction of rotation, at
Figure DEST_PATH_GDA0000134382590000066
In the vector, the first side corresponding to the coincident vector is DC, which is the next side of the current minimum enclosing contour line. At this time, judge whether DC is the same as the current curve AD, and if it is different, judge whether (DC, C) is Already marked, if not marked, then transfer (DC, C) to step ②;

步骤②与步骤③的循环过程可以依次得到组合(CB,B)、(BA,A)和(AD,D),此时(AD,D)中的曲线与当前曲线AD相同,可以判断当前得到的最小包围轮廓为AD、DC、CB和BA,即ABCD。  The cyclic process of step ② and step ③ can be combined (CB, B), (BA, A) and (AD, D) sequentially. At this time, the curve in (AD, D) is the same as the current curve AD, and it can be judged that the currently obtained The minimum enclosing contours of are AD, DC, CB and BA, namely ABCD. the

步骤9、循环采用步骤8中的方法就可以得到所有的最小包围轮廓,删除其中面积最大的轮廓。遍历每一个最小包围轮廓得到其中心点,然后通过该中心点,做与腹板面垂直的直线,若与“Join.1”特征不相交,那么该最小包围轮廓为特征重构结果,即有效最小包围轮廓,如图13所示得到的腹板驱动几何以及所生成的腹板加工刀轨。  Step 9, cyclically adopt the method in step 8 to obtain all the minimum enclosing contours, and delete the contour with the largest area. Traverse each minimum enclosing contour to get its center point, and then make a straight line perpendicular to the web surface through the center point, if it does not intersect with the "Join.1" feature, then the minimum enclosing contour is the result of feature reconstruction, that is, valid The minimum enclosing contour, the resulting web driving geometry and the resulting web machining toolpath are shown in Fig. 13. the

Claims (8)

1.一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于包括以下步骤:1. A method for automatically reconfiguring the geometry of an aircraft structural part groove feature web machining drive, characterized in that it comprises the following steps: 步骤1、结合一个槽特征的所有侧面、下陷面和转角面,标记为JOIN.1;Step 1. Combine all sides, sunken faces and corner faces of a groove feature, marked as JOIN.1; 步骤2、根据JOIN.1中所有面之间的邻接关系,提取其边界,标记为:BOUNDARY.1;Step 2. According to the adjacency relationship between all faces in JOIN.1, extract its boundary, marked as: BOUNDARY.1; 步骤3、结合腹板面和腹板外环底角面,标记为:JOIN2;Step 3. Combine the web surface and the bottom corner surface of the outer ring of the web, mark it as: JOIN2; 步骤4、根据JOIN.2中所有面之间的邻接关系,提取其边界,标记为:BOUNDARY.2;Step 4. According to the adjacency relationship between all faces in JOIN.2, extract its boundary, marked as: BOUNDARY.2; 步骤5、结合BOUNDARY.1和BOUNDARY.2中的所有边为一整体,标记为:JOIN.3;Step 5. Combine all edges in BOUNDARY.1 and BOUNDARY.2 into a whole, marked as: JOIN.3; 步骤6、筛选JOIN.3中的边,剔除不需要的边;Step 6. Filter the edges in JOIN.3 and eliminate unnecessary edges; 步骤7、在草图环境下,将筛选后的JOIN.3中的边向腹板面投影,求得投影后边与边的交点,并利用交点打断相交的边,处理后的结果标记为SKETCH.1;Step 7. In the sketch environment, project the edge in the filtered JOIN.3 to the web surface, obtain the intersection point between the projected edge and the edge, and use the intersection point to break the intersecting edge. The processed result is marked as SKETCH. 1; 步骤8、基于投影和打断后的所有点和边,构造含有边、点以及边与点信息的属性边点图;Step 8. Based on all points and edges after projection and interruption, construct an attribute edge-point graph containing edge, point, and edge-to-point information; 步骤9、计算出属性边点图中所有最小包围轮廓,最小包围轮廓定义为一组首尾相连的彼此不相交的平面曲线;Step 9, calculate all the minimum enclosing contours in the attribute edge point graph, and the minimum enclosing contours are defined as a group of plane curves that are connected end to end and do not intersect with each other; 步骤10、从所有最小包围轮廓得到有效的最小包围轮廓,即为最终的腹板轮廓加工驱动几何。Step 10. Obtain an effective minimum enclosing contour from all the minimum enclosing contours, which is the driving geometry for the final web contour machining. 2.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述步骤2的具体步骤是:①按照顺序逐个取出JOIN.1中的面;②提取该面的外环边界;③按照顺序逐个取出外环边界中的边;④判断该边是否属于JOIN.1中其它面的外环边,若是,则返回步骤③,否则,该边线属于JOIN.1的边界,将其列入BOUNDARY.1。2. The method for automatically reconstructing the geometry of a groove feature web of an aircraft structure as claimed in claim 1, wherein the specific steps of the step 2 are: ① Take out the JOIN.1 one by one in order ② Extract the outer ring boundary of the face; ③ Take out the edges in the outer ring boundary one by one in order; ④ Determine whether the edge belongs to the outer ring edge of other faces in JOIN.1, if so, return to step ③, otherwise, the Sidelines belong to the border of JOIN.1, which includes it in BOUNDARY.1. 3.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述的筛选JOIN.3的边的方法是:①剔除JOIN.3中相同的边;②剔除垂直于腹板面的直边。3. A method for automatic geometry reconstruction driven by machining of groove feature webs of aircraft structural parts as claimed in claim 1, characterized in that, the method for screening the edges of JOIN.3 is: ① Eliminate JOIN.3 The same edge; ② Remove the straight edge perpendicular to the web surface. 4.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述步骤7的具体步骤是:①将得到的三维边向腹板平面投影,得到投影曲线;②对于完全重合的曲线,只保留一条,对于部分重合的曲线,求出重合部分并且只保留一条;③求出曲线之间所有的交点,在每一个交点处将相应的曲线打断成两条曲线,最终得到一个网状的曲线列。4. The method for automatically reconstructing the geometry of a grooved feature web of an aircraft structure as claimed in claim 1, wherein the specific steps of step 7 are: Projection to get the projected curve; ②For the completely overlapping curves, only keep one, for the partially overlapping curves, find the overlapping part and keep only one; ③Find all the intersection points between the curves, and at each intersection point the corresponding The curve breaks into two curves, resulting in a grid-like column of curves. 5.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述步骤8的具体步骤是:①定义点类MyVertex,成员变量包括点的数学表示、点的拓扑表示以及与点相连的拓扑边列;②定义边类MyEdge,成员变量包括边的拓扑表示、边的特征表示、边的开闭口属性标识、起始点、终止点;③新建一个MyVertex类的列表,标记为:MYVERTEX_LIST,新建一个MyEdge类的列表,标记为:MYEDGE_LIST;④按照顺序逐个取出SKETCH.1中的边;⑤新建一MyEdge类的对象,将当前边的属性填入对应的成员变量中,并且将该对象列入MYEDGE_LIST中;⑥取出当前边的起始点,标记为STARTPOINT;判断STARTPOINT是否为MYVERTEX_LIST中的成员,若是,则跳至第⑦步,否则新建一MyVertex类的对象,将STARTPOINT的属性填入对应的成员中并且将该对象列入MYVERTEX_LIST中;⑦取出当前边的终止点,标记为ENDPOINT;判断ENDPOINT是否为MYVERTEX_LIST中的成员,若不是则新建一个MyVertex类的对象,将ENDPOINT的属性填入对应的成员变量中,并且将该对象列入MYVERTEX_LIST中。5. A method for automatic geometry reconstruction driven by machining of groove feature webs of aircraft structural parts as claimed in claim 1, characterized in that, the specific steps of step 8 are: ① define the point class MyVertex, and the member variables include point The mathematical representation of the point, the topological representation of the point, and the topological edge column connected to the point; ②Define the edge class MyEdge, and the member variables include the topological representation of the edge, the feature representation of the edge, the opening and closing attribute identification of the edge, the starting point, and the ending point;③ Create a new list of MyVertex class, marked as: MYVERTEX_LIST, create a new list of MyEdge class, marked as: MYEDGE_LIST; ④ Take out the edges in SKETCH.1 one by one in order; ⑤ Create an object of MyEdge class, fill in the attributes of the current edge Enter the corresponding member variable, and list the object in MYEDGE_LIST; ⑥Take out the starting point of the current edge and mark it as STARTPOINT; judge whether STARTPOINT is a member in MYVERTEX_LIST, if so, skip to step ⑦, otherwise create a new MyVertex class object, fill in the attribute of STARTPOINT into the corresponding member and list the object in MYVERTEX_LIST; ⑦Take out the end point of the current edge and mark it as ENDPOINT; judge whether ENDPOINT is a member in MYVERTEX_LIST, if not, create a new MyVertex For the object of the class, fill in the attribute of ENDPOINT in the corresponding member variable, and list the object in MYVERTEX_LIST. 6.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述步骤9的具体步骤是:6. The method for automatically reconstructing the geometry of a groove feature web of an aircraft structural part according to claim 1, wherein the specific steps of the step 9 are: ①在属性边点图中任取一段曲线li,取li的一个顶点Mi(x0,y0,z0)为当前结点,标记当前曲线与当前结点的组合,记为(li,Mi);①Choose a section of curve l i in the attribute edge-point graph, take a vertex M i (x 0 , y 0 , z 0 ) of l i as the current node, and mark the combination of the current curve and the current node, denoted as ( l i , M i ); ②将组合(li,Mi)的点Mi作为曲线段的起点,假设曲线li在点Mi的切矢为
Figure FDA0000100030890000021
与当前结点Mi连接的其他线段的切矢
Figure FDA0000100030890000022
② Take the point M i of the combination (l i , M i ) as the starting point of the curve segment, assuming that the tangent vector of the curve l i at the point M i is
Figure FDA0000100030890000021
Tangent vectors of other line segments connected to the current node M i
Figure FDA0000100030890000022
③记腹板外法向为定义的旋转方向为那么
Figure FDA0000100030890000026
绕点Mi,以为起始方向旋转,在矢量中,与其重合的矢量相对应的第一条边即为当前最小包围轮廓线的下一条边,记为li1,取li1的另外一个顶点,记为Mi1,此时判断li1是否与li相同,如果不同则判断(li1,Mi1)是否已经标记,若没有标记,则将(li1,Mi1)赋值给(li,Mi)转入步骤②;
③Record the outer normal direction of the web as definition The direction of rotation is So
Figure FDA0000100030890000026
Around the point M i , take is the starting direction of rotation, at In the vector, the first edge corresponding to the coincident vector is the next edge of the current minimum enclosing contour line, which is denoted as l i1 , and the other vertex of l i1 is denoted as M i1 , at this time, judge whether l i1 is Same as l i , if different, judge whether (l i1 , M i1 ) has been marked, if not, assign (l i1 , M i1 ) to (l i , M i ) and go to step ②;
④取li的另一个顶点为当前结点Mi′(x0′,y0′,z0′),判断(li,Mi′)是否已经标记,如果没有标记,则将(li,Mi′)赋值给(li,Mi)转入步骤②;④ Take another vertex of l i as the current node M i ′(x 0 ′, y 0 ′, z 0 ′), judge whether (l i , M i ′) has been marked, if not, set (l i , M i ′) is assigned to (l i , M i ) and transferred to step ②; ⑤得到草图中所有的最小包围轮廓;⑤ Obtain all the minimum enclosing contours in the sketch;
7.如权利要求6所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,判断所述
Figure FDA0000100030890000029
矢量中,与
Figure FDA00001000308900000210
第一个相重合的矢量的具体步骤是:
7. The method for automatically reconfiguring the geometry of a grooved feature web of an aircraft structure as claimed in claim 6, characterized in that, judging the
Figure FDA0000100030890000029
in vector, with
Figure FDA00001000308900000210
The specific steps for the first coincident vector are:
①以Mi为圆心,半径为1做圆,该圆与
Figure FDA00001000308900000211
相交于点
Figure FDA00001000308900000212
Figure FDA00001000308900000213
矢量相交于点 L n = M i + r n → ;
① Take M i as the center and make a circle with a radius of 1. The circle and
Figure FDA00001000308900000211
intersect at point
Figure FDA00001000308900000212
and
Figure FDA00001000308900000213
vector intersects at point L no = m i + r no &Right Arrow; ;
②以L0为起点构造n个向量 V → 1 = L 1 - L 0 = r 1 → - r 0 → , V → 2 = L 1 - L 0 = r 2 → - r 0 → , . . . , V → n = L n - L 0 = r n → - r 0 → ; ② Construct n vectors starting from L 0 V &Right Arrow; 1 = L 1 - L 0 = r 1 &Right Arrow; - r 0 &Right Arrow; , V &Right Arrow; 2 = L 1 - L 0 = r 2 &Right Arrow; - r 0 &Right Arrow; , . . . , V &Right Arrow; no = L no - L 0 = r no &Right Arrow; - r 0 &Right Arrow; ; ③然后分别计算
Figure FDA0000100030890000035
Figure FDA0000100030890000036
向量之间的夹角,最小夹角对应的矢量即为与第一个相重合的矢量;
③ Then calculate separately
Figure FDA0000100030890000035
and
Figure FDA0000100030890000036
The angle between the vectors, the vector corresponding to the minimum angle is the the first coincident vector;
8.如权利要求1所述的一种飞机结构件槽特征腹板加工驱动几何自动重构的方法,其特征在于,所述步骤10的具体步骤是:8. The method for automatically reconstructing geometry driven by machining of groove feature webs of aircraft structural parts as claimed in claim 1, characterized in that, the specific steps of step 10 are: ①得到的所有最小包围轮廓可以表示为:LOOP0,LOOP1,...,LOOPn;① All the minimum enclosing contours obtained can be expressed as: LOOP0, LOOP1, ..., LOOPn; ②排除面积最大的最小包围轮廓LOOPi(0≤i≤n),剩余的最小包围轮廓可以表示为:LOOP0,LOOP1,...LOOPi-1,LOOPi+1,...,LOOPn;② Excluding the minimum enclosing contour LOOPi (0≤i≤n) with the largest area, the remaining minimum enclosing contours can be expressed as: LOOP0, LOOP1, ... LOOPi-1, LOOPi+1, ..., LOOPn; ③遍历剩余的最小包围轮廓,计算当前最小包围轮廓中心点,过中心点做垂直腹板面的直线,若该直线不与JOIN.1相交,则当前最小包围轮廓即为有效最小包围轮廓。③ Traverse the remaining minimum enclosing contours, calculate the center point of the current minimum enclosing contour, and make a straight line perpendicular to the web surface through the center point. If the straight line does not intersect JOIN.1, the current minimum enclosing contour is the effective minimum enclosing contour.
CN 201110317973 2011-10-19 2011-10-19 Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure Active CN102436217B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201110317973 CN102436217B (en) 2011-10-19 2011-10-19 Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201110317973 CN102436217B (en) 2011-10-19 2011-10-19 Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure

Publications (2)

Publication Number Publication Date
CN102436217A true CN102436217A (en) 2012-05-02
CN102436217B CN102436217B (en) 2013-11-06

Family

ID=45984320

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201110317973 Active CN102436217B (en) 2011-10-19 2011-10-19 Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure

Country Status (1)

Country Link
CN (1) CN102436217B (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102789200A (en) * 2012-08-21 2012-11-21 南京航空航天大学 Integrated airplane structural part numerical-control machining capacity test model and application thereof
CN102922013A (en) * 2012-10-25 2013-02-13 南京航空航天大学 Cavity-characteristic-based high-efficiency rough machining method of aircraft structural part
CN103336485A (en) * 2013-06-18 2013-10-02 南京航空航天大学 Rapid generating method of milling path of web of airplane structural member
CN103995497A (en) * 2014-03-19 2014-08-20 沈阳飞机工业(集团)有限公司 Aircraft structural part complex curved surface identification method based on main surface expansion
CN105234466A (en) * 2015-10-28 2016-01-13 成都飞机工业(集团)有限责任公司 Slot feature side milling machining tool path generating method
CN111125836A (en) * 2019-12-23 2020-05-08 南京工业大学 Automatic construction method for web processing area of aircraft structural part based on image
CN111397560A (en) * 2020-03-06 2020-07-10 深圳力合精密装备科技有限公司 Method and device for acquiring theoretical value of square groove, computer equipment and storage medium
CN112230602A (en) * 2020-09-09 2021-01-15 广州中望龙腾软件股份有限公司 Cavity secondary rough cutter path planning method and device and storage medium

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04295903A (en) * 1991-03-26 1992-10-20 Matsushita Electric Works Ltd Method for numerical control data origination
CN101738982A (en) * 2009-12-10 2010-06-16 沈阳飞机工业(集团)有限公司 Airplane complex construction member roughing unit automatic building method
CN101763069A (en) * 2009-12-17 2010-06-30 沈阳飞机工业(集团)有限公司 Identification method of machining characteristics of complex parts of airplane

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04295903A (en) * 1991-03-26 1992-10-20 Matsushita Electric Works Ltd Method for numerical control data origination
CN101738982A (en) * 2009-12-10 2010-06-16 沈阳飞机工业(集团)有限公司 Airplane complex construction member roughing unit automatic building method
CN101763069A (en) * 2009-12-17 2010-06-30 沈阳飞机工业(集团)有限公司 Identification method of machining characteristics of complex parts of airplane

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
胡俊志: "飞机结构件槽腔特征数控编程技术的研究与实现", 《中国优秀硕士学位论文全文数据库》 *
谭丰: "飞机结构件筋特征快速数控编程技术研究与实现", 《中国优秀硕士学位论文全文数据库》 *

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102789200B (en) * 2012-08-21 2014-04-09 南京航空航天大学 Integrated airplane structural part numerical-control machining capacity test model and application thereof
CN102789200A (en) * 2012-08-21 2012-11-21 南京航空航天大学 Integrated airplane structural part numerical-control machining capacity test model and application thereof
CN102922013A (en) * 2012-10-25 2013-02-13 南京航空航天大学 Cavity-characteristic-based high-efficiency rough machining method of aircraft structural part
CN103336485A (en) * 2013-06-18 2013-10-02 南京航空航天大学 Rapid generating method of milling path of web of airplane structural member
CN103336485B (en) * 2013-06-18 2015-04-22 南京航空航天大学 Rapid generating method of milling path of web of airplane structural member
CN103995497B (en) * 2014-03-19 2017-09-08 沈阳飞机工业(集团)有限公司 The complex-curved recognition methods of aircraft structure extended based on interarea
CN103995497A (en) * 2014-03-19 2014-08-20 沈阳飞机工业(集团)有限公司 Aircraft structural part complex curved surface identification method based on main surface expansion
CN105234466A (en) * 2015-10-28 2016-01-13 成都飞机工业(集团)有限责任公司 Slot feature side milling machining tool path generating method
CN105234466B (en) * 2015-10-28 2018-03-16 成都飞机工业(集团)有限责任公司 A kind of cavity feature Flank machining knife rail generating method
CN111125836A (en) * 2019-12-23 2020-05-08 南京工业大学 Automatic construction method for web processing area of aircraft structural part based on image
CN111125836B (en) * 2019-12-23 2023-10-20 南京工业大学 Automatic construction method for web processing area of aircraft structural member based on image
CN111397560A (en) * 2020-03-06 2020-07-10 深圳力合精密装备科技有限公司 Method and device for acquiring theoretical value of square groove, computer equipment and storage medium
CN111397560B (en) * 2020-03-06 2021-05-07 深圳力合精密装备科技有限公司 Method and device for acquiring theoretical value of square groove, computer equipment and storage medium
CN112230602A (en) * 2020-09-09 2021-01-15 广州中望龙腾软件股份有限公司 Cavity secondary rough cutter path planning method and device and storage medium
CN112230602B (en) * 2020-09-09 2021-10-12 广州中望龙腾软件股份有限公司 Cavity secondary rough cutter path planning method and device and storage medium

Also Published As

Publication number Publication date
CN102436217B (en) 2013-11-06

Similar Documents

Publication Publication Date Title
CN102436217B (en) Method for reconstructing web processing drive geometry of slot characteristic of aircraft structure
CN103699055B (en) Aircraft structure intelligent numerical control machining prgraming system and method
CN103336485B (en) Rapid generating method of milling path of web of airplane structural member
CN101738982B (en) Airplane complex construction member roughing unit automatic building method
CN102411333B (en) Fast numerical control machining process system for complex parts of airplane
CN110349252A (en) A Method of Constructing Actual Machining Curves of Small Curvature Parts Based on Point Cloud Boundaries
CN103365243B (en) Method for rapidly generating corner side milling process path
CN112926207B (en) Method and system for automatically constructing editable model of equal-geometry topological optimization result
CN104217063B (en) Emulation design method for steel rail rolling pass
JP4512754B2 (en) Process design support system and process design support method
CN107562015B (en) Process geometric model construction method based on numerical control machining programming
CN110188423A (en) A kind of linear engineering structure fast B IM modeling method based on FEM meshing
CN103454974A (en) Intelligent numerical control programming method driven by complex component process scheme
CN105184013B (en) A kind of process model positive sequence generation method and device based on cutting body
CN104375464A (en) Aircraft skin milling efficient machining path automatic generating method
CN102629287A (en) Automatic identification method based on standard for the exchange of product model data-compliant numerical control data interface (STEP-NC) intersection features
CN108073747A (en) Aircraft structure Three Dimensional Design Model quality detecting system and method
CN106780763A (en) Three-dimensional surface intersection section geometric figure and the space broken line method of development
CN106021669A (en) Parametric design system and method for tire patterns
TW202022653A (en) Automatic generation system for machining parameter
CN106204736B (en) Unfolding lofting manufacturing method of three-dimensional surface triangle unfolding method
CN114002996B (en) A smoothing method for continuous five-axis path transfer of hybrid robot C3
CN106814690B (en) A method for determining smooth tool path in triangular mesh milling
CN110706353A (en) Parametric modeling method of device skin self-supporting structure
CN110276161B (en) Method for creating tunnel lining segment model template based on CATIA software rule

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant
TR01 Transfer of patent right

Effective date of registration: 20200331

Address after: 215104 No. 7, North Guandu Road, Yuexi Street, Wuzhong River, Suzhou City, Jiangsu Province

Patentee after: JIANGSU MAIXINLIN AVIATION TECHNOLOGY Co.,Ltd.

Address before: Yudaojie Baixia District of Nanjing City, Jiangsu province 210016 No. 29 box 357

Patentee before: Nanjing University of Aeronautics and Astronautics

TR01 Transfer of patent right