重型火箭发动机机架大口径支撑杆成形工艺试验

Forming Technology Test of Heavy Lift Launch Vehicle Engine Frame with Large Diameter Support Rod

为保证重型火箭发动机机架大口径支撑杆零件的尺寸精度及控制零件减薄率,对其成形进行工艺仿真和研究。采取回程旋压的方式对管子进行缩口,利用ABAQUS对收口旋压时不同进给量的影响进行模拟。采用DC-1600CNC旋压设备结合自主设计的旋轮及加紧装置进行工艺试验,并通过试验优化旋压转速、旋压道次及单道次下压量等工艺参数。结果表明:该方法能成功得到合格零件,保证零件施压角度偏差为-1°,对称度偏差为0.3 mm,壁厚范围控制在7.3~7.6 mm,同时旋压区未出现明显的褶皱。

In order to ensure the dimensional accuracy and control the thinning rate of the large diameter support rod of heavy rocket engine frame,the forming process simulation and research were carried out.The tube was necked by return spinning,and ABAQUS was used to simulate the effect of different feed rate on the necking spinning.DC-1600CNC spinning equipment combined with self-designed spinning wheel and clamping device was used for process test,and the process parameters such as spinning speed,spinning pass and single pass reduction were optimized through the test.The results show that the method can successfully obtain qualified parts,ensure that the pressure angle deviation is-1°and the symmetry deviation is 0.3 mm,the wall thickness range is 7.3-7.6 mm,and there is no obvious wrinkle in the spinning area.