论短肢剪力墙的轴压比限值

在理论方面,短肢剪力墙的研究尚处在探索阶段,缺少系统的研究,有关短肢剪力墙结构的轴压比对抗剪性能的影响分析还很不完善。在理论分析的基础上,确定了用以判断构件大、小偏压状态的界限轴压比,得到了为保证T形截面短肢剪力墙构件具有一定延性的轴压比限值。     

用有限元强度折减法进行加筋土挡土墙稳定性分析

加筋土挡土墙边坡是一种新型的边坡加固形式,传统的理论分析主要是考虑力的平衡关系,因此还有不少的缺陷,而有限元分析不仅满足力与位移的平衡关系,而且考虑了筋带与土体的协调变形作用,模拟的结果能使人们方便地掌握挡墙的整体与局部变化。结合某加筋土挡土墙的实例,利用有限元对其进行了数值模拟,用强度折减法计算了边坡的安全系数,并与极限平衡进行比较,对类似的工程有一定的指导作用。     

土工格栅加筋土挡墙稳定性影响因素敏感性分析

以灰关联分析法为手段,通过有限元强度折减法计算加筋土挡墙的稳定安全系数。结合水富—麻柳湾高速公路的土工格栅加筋土挡墙实际工程,分析了各因素对土工格栅加筋土挡墙稳定影响的敏感性,按大小依次为：内摩擦角、筋土间摩擦系数、粘聚力、筋带长度、筋带轴向拉伸刚度、筋带间距和填土密度。建议设计中,如果条件许可应优先选择摩擦角和粘聚力较高的填料,当填料受限制时,要提高加筋土挡墙的稳定性可以优先考虑选择与填土有较高摩擦系数和轴向拉伸刚度较大的土工格栅进行设计。     

Study on performance degradation and failure analysis of machine gun barrel

An increase in the use of the gun barrel will cause wear of the inner wall, which reduces the muzzle velocity and the spin rate of the projectile. The off-bore flight attitude and trajectory of the projectile also change, affecting the shooting power and the accuracy. Exterior ballistic data of a high-speed spinning projectile are required to study the performance change. Therefore, based on the barrel's accelerated life test, the whole process of projectile shooting is reproduced using numerical simulation technology, and key information on the ballistic performance change at each shooting stage are acquired. Studies have shown that in the later stages of barrel shooting, the accuracy of shooting has not decreased significantly. However, it is found that the angle of attack of the projectile increases as the wear of the barrel increases. The maximum angle of attack reaches 0.106 rad when the number of shots reaches 4300. Meanwhile, elliptical bullet hole has appeared on the target at this shooting stage. Through combining external ballistic theory with simulation results, the primary reason of this phenomenon is found to be a significant decrease in the muzzle spin rate of the projectile. At the end of the barrel life, the projectile muzzle spin rate is 57.5% lower than that of a barrel without wear.     

不同射流状态下射流气体与高超声速主流相互作用影响

为研究不同射流状态对高超声速飞行器气动加热的影响,对高超声速来流条件下方孔和圆孔横向射流模型进行数值模拟,讨论射流压强、射流速度及射流方向对主流流场的影响,得到了不同射流状态下流场结构、壁面温度热流分布及壁面中心线温度热流变化。结果表明:射流在一定程度上能缓解壁面气动加热情况,壁面引射效果更好,壁面引射速度1 m·s~(-1)时壁面热流降低接近三分之二。在高速(Ma1)射流情况下,适当增大压强和速度,均会使得射流下游的冷却效果加强;在中低速(Ma0.6)射流情况下,射流基本上不改变主流流场而在边界层内流动,流速越大,冷却范围越大,冷却效果也相对较好。射流方向与主流方向夹角为锐角时,利于射流孔下游降温;夹角为钝角时,利于射流孔上游降温。