基于力控技术的航空整体加强框自适应定位方法研究

Assembly-Ariented Optimization Design of Positioning Quality for Aircraft Integral Strengthening Frame

为了减弱制造差异对航空整体加强框装配定位质量的影响,解决强迫定位造成的定位过程管控性差和定位结果复现度低的难题,基于力控技术提出一种航空整体加强框自适应定位方法,按传统强迫方式完成装配定位后,在设计允许范围内调整若干坐标定位孔位置,至孔位处力载值满足自适应定位要求。针对航空整体加强框装配定位工艺对形位精度、装配应力水平的要求,量化装配定位质量评价标准,基于正交试验分析定位孔处力载绝对平均值和定位检测点处应力绝对平均值的变化规律,进行装配现场易于获取的力载值取代应力值的可行性研究,通过修正装配定位质量评价标准量化公式得到坐标定位孔处力载调整目标,指导航空整体加强框装配定位。

In order to reduce the influence of manufacturing differences on the assembly positioning quality of aviation integral re-inforcing frame and solve the problems of poor control of positioning process and low repeatability of positioning results caused by forced positioning,an adaptive positioning method of aviation integral reinforcing frame is proposed based on force control tech-nology.First,after the assembly positioning is completed according to the traditional forced method,the position of several coor-dinate positioning holes is adjusted within the allowable range of design,and the force load value at the hole position meets the adaptive positioning requirements.Second,aiming at the requirements of shape and position accuracy and assembly stress level in the assembly positioning process of aviation integral reinforcing frame,the evaluation standard of assembly positioning quality is quantified.Then,based on the orthogonal test,the variation law of the absolute average value of force load at the positioning hole and the absolute average value of stress at the positioning detection point is analyzed,and the feasibility study of replacing the stress value with the force load value easily obtained at the assembly site is carried out.Finally,the force load adjustment tar-get at the coordinate positioning hole is obtained by modifying the quantitative formula of the assembly positioning quality evalu-ation standard to guide the assembly positioning of aviation integral reinforcing frame.