三坐标定位器部件刚度配置方法

Stiffness parameter configuration of cartesian positioner components

为满足机身调姿工装的定位精度要求并兼顾调姿工装的制造工艺、成本等要求,建立三坐标定位器部件刚度配置与机身位姿误差、变形之间的关系模型,提出三坐标定位器的部件刚度配置方法,给出三坐标定位器部件刚度配置的评价标准与流程.对机身的位姿误差、变形进行参数化定义,将调姿工装有限元模型与定位器空间定位误差模型结合,用于计算机身的位姿误差、变形.以典型的五次多项调姿路径为例,计算不同的刚度配置条件下机身的位姿误差、变形,并进行正交试验分析,得到三坐标定位器部件刚度配置的约束条件,以三坐标定位器的重量为优化目标,给出一种刚度配置.计算结果表明,经刚度配置优化后,三坐标定位器的重量可减少2.1t.

To guarantee the positioning accuracy of fuselage pose adjustment toolings, a relation model between stiffness parameters configuration of Cartesian positioner components and pose error and deformation of fuselage was established. A method for the stiffness parametersconfiguration of Cartesian positionerswas proposed in order to meet the requirements of manufacturing technology and cost. Evaluation criterion and procedure for stiffness parameter configuration were also proposed. The parameters which describe the pose error and deformation of fuselage were defined. The pose error and deformation of fuselage were calculated by combining positioning error model of Cartesian positioned and finite element analysis model configuration, the pose error quintic polynomial trajectory. of Cartesian positioned was of fuselage pose adjustment toolings. Under different stiffness parameters and deformation of fuselage were calculated by orthogonal test according to Consequently obtained. Th obtained for minimum weight. The results optimizingstiffness parameter configuration the constraint condition for stiffness e stiffness parameter configuration P of arameter configuration the show that the positioner can reduce a weight components was of 2.1 tons after