异型件面片缠绕成型轨迹规划的研究
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摘要
复合材料以其轻质高强度、耐腐蚀等优点,在航空航天、军工业、民用化工等领域的应用范围不断扩大,需求量不断增加,复合材料纤维缠绕技术作为复合材料的一项重要成型技术近年来被广泛关注。缠绕构件已经广泛应用于上述各个领域,逐渐成为各种设备或生产线上不可或缺的重要组成部分。
由于国外缠绕技术的起步比我国早,缠绕理论和软件总体上都比我国现有技术先进,已经实现了各种回转体和一般异型件的缠绕成型理论分析和软件编程,并实现了机械化的生产。我国纤维缠绕轨迹的设计都是基于传统的参数化缠绕理论,该理论的设计是基于芯模的轮廓方程,适于回转体或可以用方程描述的芯模的缠绕轨迹设计与规划,并能够设计出理想的稳定缠绕轨迹;但是对于叶片、飞机进气道、三通管等不能用方程表达的异型体构件,该理论不再适用。目前国内使用的非回转体复合材料构件均为手糊成型,产品强度、稳定性和加工效率均得不到保证。随着异型件在各个领域的广泛应用,这种落后的加工方式已经远不能够满足生产的需要,因此,如何设计与规划异型体构件的缠绕轨迹已经成为亟待解决的问题。
本文针对异型体构件轮廓不能用方程描述的特点,提出了一种基于芯模表面网格节点的缠绕理论—面片缠绕理论,以解决一般异型件的缠绕成型问题。面片缠绕理论的设计理念是首先对芯模网格化,取其表面网格节点,然后依据不滑线、不架空等稳定缠绕的必要条件和空间几何、微分几何知识来确定缠绕轨迹落纱点,并进行纤维缠绕轨迹整体规划。由于采用面片缠绕理论得到的是离散点轨迹,传统的后置处理方法已经不再适用,因此本文提出了一种新的复杂曲面纤维缠绕轨迹后置处理方法,它依据空间几何知识和网格节点来近似求取各向量,有效地解决了离散落纱点的后置处理问题。
为验证面片缠绕理论和复杂曲面缠绕轨迹后置处理方法,本文采用SQL Server对芯模表面网格节点数据进行排序、查询等管理,利用VC++与SQL Server接口访问数据库获取节点数据,并编制缠绕仿真和缠绕轨迹后置处理程序。对于组合回转体,分别采用传统参数化缠绕理论和面片缠绕理论对缠绕成型采用统一的缠绕轨迹规划,一次性完成多种回转体的缠绕成型,既保证了强度又避免了各个单一回转体缠绕完毕再组合的步骤;对于叶片,采用方程近似描述其轮廓,然后分别采用两种缠绕方法进行缠绕线型规划;对于飞机进气道,由于其表面存在局部凹曲面,利用面片缠绕理论对其进行缠绕轨迹规划和缠绕实验,利用实验结果进行可缠性分析;对于三通管,采用面片缠绕理论,将三通管过渡部分分为三个区域,并分别进行缠绕轨迹设计和规划,然后将所有线型连接起来实现单纤维一次性缠绕布满。
With the promise of significant weight reduction and the advantages of high intensity and erosion resistance, the composite military has been widely used in the fields of aviation and aerospace industry, military industry and civil industry. The need for the composite material products becomes an ever increasing necessity. The filament winding, as an important composite material forming technology, has drawn much more attention in recent years. Winding component has been widely used throughout the industry fields and it has become an essential part of various equipments and manufacturing lines.
The filament winding technology starts first in the western country. Generally speaking, their winding theory and software are more advanced than us. They have realized various gyration object and abnormal form object winding theory analysis, software programming and machine manufacturing. In China, the filament winding trajectory design is derived from the parametric winding theory, which is based on the mould outline formulation. The parametric winding theory is used to design the winding trajectory of gyration object or the mould which can be described by the formulation. Generally speaking, it can have an ideal and stable winding trajectory. However, as for the abnormal form objects such as the lamina, airplane inlet and T-shape mould, which can not be described by the formulation, this theory can’t run well. Now, the non-gyration composite material winding products are made by hand paste, which can not ensure the product’s strength, stability and manufacture efficiency. With the application of the abnormal form objects in various fields, this kind of manufacturing method is out of date. Therefore, how to design the abnormal form object winding trajectory has become an urgent problem.
Because the abnormal form object can not be described by the formulation, this dissertation proposes the patch winding theory to solve this problem. The patch winding theory is based on the mesh nodes on the mould surface. The following is the patch winding theory. Firstly, the mould is meshed, and then, the mesh nodes on the surface can be output. Based on the space geometry, differential geometry, and the stable winding requirements of non-slip line and non-bridge condition, the doffing points of the winding trajectory are determined, and then, the overall winding trajectory design is programmed. Because the trajectory got by the patch winding theory is the disperse point trajectory, the traditional post disposal method can not manage this trajectory. Therefore, this dissertation presents a new post disposal method for the complex surface winding trajectory. It gets every approximate vector based on the space geometry and the mesh nodes. It can solve the problem of disperse doffing point post disposal efficiently.
In order to verify the patch winding theory and the complex surface filament winding post disposal method, SQL Server is used to sort order and inquiry the mesh node data in this dissertation. The node data are got by visiting the database SQL Server with VC++. Then, the winding simulation and the winding trajectory post disposal can be put in practice. As for the assembled gyration object, this dissertation adopts one uniform winding trajectory design by using the traditional parametric winding theory and the patch winding theory respectively. Several kinds of gyration object can be wound with one winding trajectory, which can ensure the strength and avoid the step of assembling all the different winding gyration products into one. For the lamina, this dissertation uses the formulation to describe its outline approximately. The lamina is wound by the two methods respectively. For the airplane inlet, the patch winding method is used to design the winding trajectory and carry out the winding experiments. According to the experiment effects, the winding probability is analyzed for partial concave surface. For the T-shape object, according to the patch winding theory, this dissertation divides the transitional part into three sections and designs the winding trajectories respectively. Then, it unifies all the trajectories into one trajectory and it realizes the bestrewed winding by using one singular filament.
由于国外缠绕技术的起步比我国早,缠绕理论和软件总体上都比我国现有技术先进,已经实现了各种回转体和一般异型件的缠绕成型理论分析和软件编程,并实现了机械化的生产。我国纤维缠绕轨迹的设计都是基于传统的参数化缠绕理论,该理论的设计是基于芯模的轮廓方程,适于回转体或可以用方程描述的芯模的缠绕轨迹设计与规划,并能够设计出理想的稳定缠绕轨迹;但是对于叶片、飞机进气道、三通管等不能用方程表达的异型体构件,该理论不再适用。目前国内使用的非回转体复合材料构件均为手糊成型,产品强度、稳定性和加工效率均得不到保证。随着异型件在各个领域的广泛应用,这种落后的加工方式已经远不能够满足生产的需要,因此,如何设计与规划异型体构件的缠绕轨迹已经成为亟待解决的问题。
本文针对异型体构件轮廓不能用方程描述的特点,提出了一种基于芯模表面网格节点的缠绕理论—面片缠绕理论,以解决一般异型件的缠绕成型问题。面片缠绕理论的设计理念是首先对芯模网格化,取其表面网格节点,然后依据不滑线、不架空等稳定缠绕的必要条件和空间几何、微分几何知识来确定缠绕轨迹落纱点,并进行纤维缠绕轨迹整体规划。由于采用面片缠绕理论得到的是离散点轨迹,传统的后置处理方法已经不再适用,因此本文提出了一种新的复杂曲面纤维缠绕轨迹后置处理方法,它依据空间几何知识和网格节点来近似求取各向量,有效地解决了离散落纱点的后置处理问题。
为验证面片缠绕理论和复杂曲面缠绕轨迹后置处理方法,本文采用SQL Server对芯模表面网格节点数据进行排序、查询等管理,利用VC++与SQL Server接口访问数据库获取节点数据,并编制缠绕仿真和缠绕轨迹后置处理程序。对于组合回转体,分别采用传统参数化缠绕理论和面片缠绕理论对缠绕成型采用统一的缠绕轨迹规划,一次性完成多种回转体的缠绕成型,既保证了强度又避免了各个单一回转体缠绕完毕再组合的步骤;对于叶片,采用方程近似描述其轮廓,然后分别采用两种缠绕方法进行缠绕线型规划;对于飞机进气道,由于其表面存在局部凹曲面,利用面片缠绕理论对其进行缠绕轨迹规划和缠绕实验,利用实验结果进行可缠性分析;对于三通管,采用面片缠绕理论,将三通管过渡部分分为三个区域,并分别进行缠绕轨迹设计和规划,然后将所有线型连接起来实现单纤维一次性缠绕布满。
With the promise of significant weight reduction and the advantages of high intensity and erosion resistance, the composite military has been widely used in the fields of aviation and aerospace industry, military industry and civil industry. The need for the composite material products becomes an ever increasing necessity. The filament winding, as an important composite material forming technology, has drawn much more attention in recent years. Winding component has been widely used throughout the industry fields and it has become an essential part of various equipments and manufacturing lines.
The filament winding technology starts first in the western country. Generally speaking, their winding theory and software are more advanced than us. They have realized various gyration object and abnormal form object winding theory analysis, software programming and machine manufacturing. In China, the filament winding trajectory design is derived from the parametric winding theory, which is based on the mould outline formulation. The parametric winding theory is used to design the winding trajectory of gyration object or the mould which can be described by the formulation. Generally speaking, it can have an ideal and stable winding trajectory. However, as for the abnormal form objects such as the lamina, airplane inlet and T-shape mould, which can not be described by the formulation, this theory can’t run well. Now, the non-gyration composite material winding products are made by hand paste, which can not ensure the product’s strength, stability and manufacture efficiency. With the application of the abnormal form objects in various fields, this kind of manufacturing method is out of date. Therefore, how to design the abnormal form object winding trajectory has become an urgent problem.
Because the abnormal form object can not be described by the formulation, this dissertation proposes the patch winding theory to solve this problem. The patch winding theory is based on the mesh nodes on the mould surface. The following is the patch winding theory. Firstly, the mould is meshed, and then, the mesh nodes on the surface can be output. Based on the space geometry, differential geometry, and the stable winding requirements of non-slip line and non-bridge condition, the doffing points of the winding trajectory are determined, and then, the overall winding trajectory design is programmed. Because the trajectory got by the patch winding theory is the disperse point trajectory, the traditional post disposal method can not manage this trajectory. Therefore, this dissertation presents a new post disposal method for the complex surface winding trajectory. It gets every approximate vector based on the space geometry and the mesh nodes. It can solve the problem of disperse doffing point post disposal efficiently.
In order to verify the patch winding theory and the complex surface filament winding post disposal method, SQL Server is used to sort order and inquiry the mesh node data in this dissertation. The node data are got by visiting the database SQL Server with VC++. Then, the winding simulation and the winding trajectory post disposal can be put in practice. As for the assembled gyration object, this dissertation adopts one uniform winding trajectory design by using the traditional parametric winding theory and the patch winding theory respectively. Several kinds of gyration object can be wound with one winding trajectory, which can ensure the strength and avoid the step of assembling all the different winding gyration products into one. For the lamina, this dissertation uses the formulation to describe its outline approximately. The lamina is wound by the two methods respectively. For the airplane inlet, the patch winding method is used to design the winding trajectory and carry out the winding experiments. According to the experiment effects, the winding probability is analyzed for partial concave surface. For the T-shape object, according to the patch winding theory, this dissertation divides the transitional part into three sections and designs the winding trajectories respectively. Then, it unifies all the trajectories into one trajectory and it realizes the bestrewed winding by using one singular filament.
引文
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