中文摘要：

为了探索灵巧子弹药的减速导旋伞——涡环旋转伞的充气性能和气动特性,利用任意拉格拉日-欧拉流-固耦合方法,模拟一种典型涡环旋转伞在无限质量和低速气流条件下的充气过程,得到伞衣动态变化过程、转速和投影直径时程变化曲线及充满后稳态下的流场变化特性。将充满伞衣幅的有限元模型转化为气动特性仿真模型,利用计算流体力学方法得到涡环旋转伞在低速气流作用下的气动力参数及流场流线、压力分布等特性。将两种方法得到的结果进行对比分析,结果表明：涡环旋转伞在来流12 m/s时能顺利充气展开并实现旋转,伞衣幅充满外形饱满,稳定转速约为3.3 r/s;阻力系数为1.36,大于一般结构轴对称降落伞;导旋力矩系数为0.87;流场分布具有中心对称性。

英文摘要：

To explore the inflation performance and aerodynamic characteristics of vortex ring parachute which is often used as decelerating and spinning parachute of smart ammunition, the inflation process under the conditions of infinite mass and slow flow velocity is simulated using arbitrary Lagrange-Euler method. The canopy deforming process, time-history curves of spinning rate and projected diameter and fluid domain features at steady state are obtained. The finite model of inflated canopies is transformed to a simulation model of aerodynamic characteristics. The aerodynamic force parameters, the features of ve- locity streamlines and the pressure distribution are obtained by using computational fluid dynamics meth- od. The results obtained by the two methods are compared and analyzed. The results show that the vortex ring parachute can inflate smoothly and rotateat 12 m/s. The shape of inflated canopy is plump and the steady spinning rate is about 3.3 r/s. The drag coefficient is about 1.36, which is greater than those of other typical parachutes with axial symmetry structure. The spinning moment coefficient is 0. 87. The distributions of fluid domain features are centrally symmetrical around the parachute axis.