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针对飞机结构件内型转角传统的分开加工易产生接刀痕以及转角处进给方向和刀具接触角急剧变化引起的切削力增大和刀具振动增强的问题,提出了飞机结构件内型转角一体加工工艺及其刀轨生成方法。该方法对内型和转角进行组合加工,首先计算满足接触角均匀变化的精加工所需余量和精加工刀轨,以及后续刀轨加工区域;其次在后续加工转角时通过采用最大和恒定接触角相结合的原则,循环分层加工转角,改善了加工状况。在刀轨连接处使用变螺旋曲线,保证了曲率的连续变化,减小了机床振动。切削实验表明:该刀轨改善了加工过程中的切削力和刀具振动,提高了工件表面的加工质量。
Aiming at the problem that the conventional internal machining of internal structural corners of aircraft structural parts is easy to produce cutting edges, the feeding direction at corners and the sharp changes of tool contact angle, the cutting force increases and the tool vibration increases. Process and tool path generation method. In this method, the inner shape and the corner are processed in combination. First, the finishing allowance and the finished tool path to meet the uniform variation of the contact angle and the processing area of the subsequent tool path are calculated. Secondly, the maximum and constant contact Corner of the principle of combining the loop processing corner, improve the processing conditions. The use of a spiral curve at the tool path connection ensures a continuous change in curvature and reduces machine vibration. Cutting experiments show that: the tool path to improve the cutting process and tool vibration, improve the quality of the workpiece surface processing.