摘要
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。
In order to address the issues of cutting steps induced by the separated machining of corners and profiles of aircraft structural parts as well as the increase of the cutting force and vibration due to the sharp change of the feed angle at the corner and the contact cutting angle,an integrated machining process and its tool path generation method are proposed for machining the corners and profiles in aircraft structural parts.In the proposed method,profiles and corners in one pocket are machined in one machining operation.Firstly,the allowance is calculated for finish machining which can guarantee the uniform change of the cutting angle within limits.The machining area is also obtained for subsequent tool path.Then by using the combination principle of maximum and constant contact cutting angle in corner positions,the corner material is removed evenly by multiple passes.Therefore the cutting condition is improved.Clothoid curve segments are adopted so as to smoothen the transition of the tool path,ensure the continuous change of the curvature,as well as reduce the vibration of the machine tool.The cutting experiment results show that the proposed method can improve the conditions of the cutting force,reduce vibration during machining as well as improve the surface machining quality.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2014年第9期2660-2671,共12页
Acta Aeronautica et Astronautica Sinica
基金
国家科技重大专项(2012ZX04010041)~~
关键词
飞机结构件
内型
转角
加工
切削力
aircraft structural part
profile
corner
machining
cutting force
