运载火箭动力系统试验承力环的静力试验  

Static test of support ring used in launch vehicle power system test

作　　者：沈冰妹[1] 卜玉[1] 刘瑞敏[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2014年第6期85-91,共7页Journal of Rocket Propulsion

摘　　要：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 scheme for a support ring used in a launch vehicle power system test was established to evaluate its stiffness and strength. In order to simulate the impact load of engine shutdown, the maximum load of static test was set to 2 times of the rated total thrust of the engine, including horizontal and vertical components, which were equally divided into 8 stages of load step. Twenty-seven three-direction strain measuring points and twelve axial displacement measuring points were set up to detect the stress and displacement of the key points on the ring. The measured results shows that, for the maximal load, the equivalent stress reaches 303 MPa, lower than the yield strength of the material; the axial deformation reaches 3.16 mm, lower than the allowable deformation; the maximum stress point is located on the pin holes of the legs. The change of the distance between the pin holes was measured and MT crack detection of the steel plate surface nearby was performed. The data indicates that, the support ring has enough stiffness and strength under 2 times of the rated load of power system, and can be used for the test.

关 键 词：承力环 静力试验 MT探伤 动力系统试验 运载火箭 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]