以全弹毁伤增强为目标,针对固体火箭发动机爆轰形成破片为自然破片,成型效果较差的问题,开展燃烧室壳体刻槽研究。由横向刻槽圆筒、纵向刻槽圆筒、横纵刻槽圆筒、横纵刻槽燃烧室壳体的研究顺序,分析了不同横槽、纵槽和横纵槽刻槽参数对破片成型的影响,获取适用于大直径薄壁发动机燃烧室的壳体刻槽参数,对得到的刻槽参数进行毁伤威力分析。结果表明: 在大直径薄壁圆筒的前提下,刻槽间距大于3倍壁厚可形成规则破片,刻槽间距的增加虽然会减少破片数量,但单破片质量增加,有更高的毁伤范围。槽深与槽宽参数较为接近战斗部刻槽参数,且横槽槽深会极大影响预控破片的生成,但过深的刻槽将会超过发动机壳体的安全范围,故横槽槽深可选范围较小。研究结论可为弹箭推进毁伤一体化设计提供参考依据。

With the enhancement of overall warhead damage as the research objective, this study addresses the issue of the poor formation effect of natural fragments generated by the detonation of solid rocket engines. Research is conducted on the grooving of the combustion chamber casing. Following the research sequence of transverse grooved cylinder-longitudinal grooved cylinder-transverse and longitudinal grooved cylinder-transverse and longitudinal grooved combustion chamber casing, the impact of different transverse, longitudinal, and combined transverse and longitudinal groove parameters on fragment formation is analyzed. Parameters suitable for the casing of large-diameter, thin-walled engine combustion chambers are obtained, and the damage power of the obtained groove parameters is analyzed. The results indicate that, under the premise of a large-diameter, thin-walled cylinder, a groove spacing greater than three times the wall thickness can form regular fragments. Although an increase in groove spacing reduces the number of fragments, the mass of individual fragments increases, resulting in a higher damage range. The parameters of groove depth and width are relatively close to those of warhead groove parameters, and the depth of the transverse groove significantly affects the generation of pre-controlled fragments. However, excessively deep grooves will exceed the safety range of the engine casing, hence the selectable range for transverse groove depth is relatively small. The conclusions of this study can provide a reference basis for the integrated design of projectile and rocket propulsion damage.