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SOLID ROCKET BOOSTER SEGMENT JOINT - A PARAMETRIC STUDY

机译:固体火箭助推节段-参数研究

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The solid rocket boosters are normally manufactured in segments that are independently propellant cast and laterassembled for the launch. The joint between the segments is generally a tang & clevis (tongue & groove) type jointwith shear pins having minimum clearance fit to ease the assembly. As an assembly feature, three numbers of theholes drilled in the tongue ring are slit open to ensure circumferential alignment, and hence no load is transferred atthese locations. Due to this provision, the shear pins adjacent to slit holes are the most critical ones in sharing theload. However, since these pins are in shear mode, even a small difference in the clearance in this critical pin-holeinterface, can cause a different kind of load distribution. Considering the fact that the pin & hole has a clearance fit,the load in each pin becomes indeterminate due the various possible pin and hole combinations. To address thisissue, the worst possible combination is considered for estimating the load in critical pin locations based on a 3Dfinite element model of the joint. During the developmental stage of the segment hardware many cases of deviationsare reported in the pin hole dimensions which resulted in higher variability in the load shared among the pins. Thisobservation called for a parametric 3D finite element model capable of simulating any possible combination oftolerances in the pin and hole. Apart from the pin and hole tolerance, the 3D model can also incorporate the possiblefits between the various mating diameters of the tongue and groove ring. The effect of friction in sharing the axialload is also estimated from this model. Application of experimental techniques such as strain gauging orphotoelasticity to estimate the pin loads is found not feasible in these intrinsic geometry. Hence, these finite elementmodels were extremely useful in assessing the criticality of the observed deviation in pin holes, since no otherexperimental technique could be successfully used for this purpose. This method has not only avoided unnecessaryrejections but also is helpful in proposing salvaging plans, resulting in saving of equivalent amount of monetary aswell as time resources.
机译:固体火箭助推器通常按独立的推进剂铸造工艺制造,以后再进行制造。 为发射而组装。段之间的接头通常是tang&clevis(榫舌和凹槽)型接头 剪切销具有最小的间隙,可简化装配。作为装配特征,三个数字 舌环上钻的孔被切开以确保周向对齐,因此在 这些位置。由于这一规定,与狭缝孔相邻的剪切销是共享销钉时最关键的销钉。 加载。但是,由于这些销钉处于剪切模式,因此该关键销钉孔中的间隙即使很小 接口,可能会导致另一种负载分配。考虑到销钉和孔之间有间隙配合, 由于各种可能的销钉和孔组合,每个销钉中的载荷变得不确定。为了解决这个问题 问题,考虑了最坏的组合以基于3D估算关键引脚位置的负载 关节的有限元模型。在段硬件的开发阶段,很多情况下都会出现偏差 在销孔尺寸中报告了这些值,这导致销之间共享的负载变化更大。这 观察需要一个参数3D有限元模型,该模型能够模拟以下任何可能的组合: 销和孔的公差。除了销钉和孔的公差外,3D模型还可以整合 可安装在榫舌和凹槽环的各种配合直径之间。摩擦力在轴向共享中的作用 该模型也可以估算负载。实验技术的应用,例如应变测量或 在这些固有几何形状中,无法通过光弹性来估算销钉载荷。因此,这些有限元 这些模型在评估针孔中观察到的偏差的严重性方面非常有用,因为没有其他方法可以使用 实验技术可以成功地用于此目的。这种方法不仅避免了不必要的 拒绝,但也有助于提出救助计划,从而节省了与 以及时间资源。

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