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建立了某型号运载火箭动力系统试验用承力环的非破坏性静力试验方案,以评估该承力环的强度和刚度。为模拟发动机关机时的载荷冲击,将静力试验最大载荷设定为发动机额定总推力的2倍,包含水平和垂直两个分量,均分为8个载荷步加载。在承力环上设置了27个三向应变测点和12个轴向位移测点,以监测一些关键点的应力和位移。测量结果显示,在最大载荷下,当量应力达到303 MPa,低于材料屈服强度;轴向变形达到3.16 mm,低于设计许用变形;应力最大点位于支腿销孔处。对销孔孔距的变化进行了测量,并对附近的钢板表面进行了MT探伤。数据结果表明,该承力环在两倍的动力系统试验额定载荷下有足够的强度和刚度,可用于该试验。
A non-destructive static test program was established for the test bearing ring of a certain type of rocket power system to evaluate the strength and stiffness of the bearing ring. In order to simulate the load shock when the engine is off, the maximum static test load is set to twice the rated total thrust of the engine, including both horizontal and vertical components, divided into 8 load steps. There are 27 three-way strain gauges and 12 axial displacement gauges on the bearing ring to monitor the stress and displacement of some key points. The measurement results show that under the maximum load, the equivalent stress reaches 303 MPa, which is lower than the yield strength of the material. The axial deformation reaches 3.16 mm, which is lower than the design allowable deformation. The maximum stress is located at the pin hole of the leg. The change of pinhole pitch was measured and MT flaw detection was performed on the surface of the nearby steel plate. The results show that the bearing ring has sufficient strength and stiffness at twice the rated load of the powertrain test and can be used in the test.