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本文详细介绍了化学系统分公司(OSD)研制的惯性顶级(IUS)推进系统采用的63英寸和92英寸直径的凯夫拉/环氧纤维缠绕的火箭发动机壳体的设计和试验结果。IUS 要求发动机壳体结构性能超过大型复合材料发动机壳体当前的技术水平。尤其要求 SRM—1裙的结构承载超过凯夫拉/环氧裙当前水平的50%,压力容器的性能超过当前水平的35%。至今多次全尺寸爆破压力试验表明惯性顶级发动机壳体超过了当前技术水平的要求,壳体效率(PV/W)高达1.27×10~6英寸。SRM—1结构试验在压缩线载荷—3564磅/英寸和峰值为2298磅/英寸的剪切载荷联合作用下,超过当前技术水平48%,超过要求值的18%。
This article details the design and test results for the 63-inch and 92-inch diameter Kevlar / epoxy fiber wound rocket motor housings used in the IUS propulsion system developed by the Chemical Systems Division (OSD). IUS requires that the structural performance of engine housings exceed the current state of the art of large composite engine housings. In particular, the structure of the SRM-1 skirt is required to carry more than 50% of the current level of Kevlar / epoxy skirts and the performance of pressure vessels exceeds 35% of the current level. Several full-scale burst pressure tests to date have shown that inertial top-grade engine housings surpass current state of the art requirements with housing efficiencies (PV / W) of up to 1.27 x 10-6 inches. The SRM-1 structural test exceeds the current state of the art by 48% in excess of 18% of the required value, under the combined action of compressive linear load of -3564 psi and peak shear of 2298 psi.