基于定位器的飞机大部件调姿系统静刚度

针对飞机数字化装配系统应具有良好姿态保持特性的要求,以典型的基于4个三坐标定位器支撑的飞机大部件位姿调整系统为研究对象,分析大部件在外力作用下,力与位姿变化之间的关系,建立系统的静刚度和单向刚度模型,有利于分析和评价系统的姿态保持特性.分析静刚度对系统精加工误差的影响,并得出系统设计过程中在考虑刚度要求时需要遵循的原则.采用有限元软件对模拟机身样件处于目标位姿时系统的静刚度进行计算,并与解析模型计算结果进行对比分析.结果表明,有限元法与解析法计算得到的系统静刚度基本相同,从而验证了解析模型的正确性.

Static stiffness of three-axis actuators based posture alignment system for large aircraft components

To ensure better attribute of posture-holding in digital assembly system for large aircraft components, a classical kind of posture alignment and joining system for large aircraft components based on four actuators with 3-axis support was studied. By analyzing the relationship between external load and the changes of position and orientation of large aircraft component, the analytical model of general static stiffness and single-dimensional static stiffness of system were derived. Thus, the attribute of posture-holding can be analyzed. The error analysis caused by static stiffness was carried out in the process of finish machining, and design principles considering stiffness were proposed in the process of system layout design. As for the sample of fuselage section for a given model of aircraft, the static stiffness of system was calculated by FEA software when it reached the defined nominal position and orientation. Comparison result of static stiffness computed by the analytical model and the FEA software shows that the analytical model is valid.