Study on Deformation Control Technology of X-shape Integral Panel for Spacecraft
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摘要: 针对航天器X型整体壁板在铣削过程中产生加工变形导致结构尺寸超差的问题，提出一种利用有限元仿真预估零件加工变形程度的方法来优化加工工艺方案。对壁板加工过程中的受力状态进行研究，给出了一种利用铣削轨迹获取各个方向铣削力的方法，并利用铣削力有限元仿真来预估整体壁板的加工变形程度。同时，根据优化后的工艺方案设计了分腔式真空吸附工艺装备。通过实例加工验证了该方法控制铣削变形的有效性。Abstract: In order to solve the problem of structural dimension out of tolerance caused by the milling deformation in the milling of spacecraft X-shape integral panel, a method was proposed to optimize the milling process with finite element simulation to estimate the machining deformation degree of parts. In this paper, the force state of the panel in the milling was studied, and a method to obtain the milling force in all directions with the milling trajectory was given, the milling force finite element simulation was used to estimate the milling deformation degree of integral panel. At the same time, according to the optimized process plan, the separate cavity vacuum adsorption process equipment was designed. The limitation of this method to control the milling deformation was verified by an example.
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Key words:
- integral panel /
- milling force /
- finite element simulation /
- deformation control
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表 1 不同铣削深度下铣削力仿真值
ap/mm 铣削力仿真值 铣削力比值 F合 Fx Fy Fz （Fx/F合）/仿真值 (Fy/F合）/仿真值 (Fz/F合）/仿真值 1 41 15 31 22 （0.30 ~ 0.40）/0.365 （0.85 ~ 0.95）/0.756 （0.50 ~ 0.55）/0.537 5 205 70 165 110 （0.30 ~ 0.40）/0.341 （0.85 ~ 0.95）/0.805 （0.50 ~ 0.55）/0.537 10 390 110 320 190 （0.30 ~ 0.40）/0.282 （0.85 ~ 0.95）/0.821 （0.50 ~ 0.55）/0.537 注：铣削条件n=8 000 r/min; f=6 000 mm/min; ae=1 mm；Fx/F合，Fy/F合，Fz/F合均为顺铣经验比值。 
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