中文摘要：

为提高爆炸带的展直率,确保火箭爆破器的破障效果,建立二维有限质点模型对火箭爆破器系统的飞行特性进行研究。根据力学方程、运动方程和几何连续方程,通过时间差分法对各质点的力学参数进行数值计算,并结合实验工况对火箭爆破器系统在空中飞行的力学特性进行计算分析。结果表明：在主动段中,火箭拖拽爆炸带加速运动,爆炸带保持直线拉直状态;爆炸带全部拉出后,由于阻力伞的作用,爆炸带的内力较大,仍能维持在展直状态;进入被动段后,随着火箭及爆炸带速度的下降,阻力伞对爆炸带的拉力随之下降,爆炸带在越过最高点后,下落的阶段容易发生弯曲。

英文摘要：

In order to improve the elongation of explosive belt and ensure the effect of the rocket explosive device in breaking barriers, the flight characteristic of the rocket explosive device was studied by establishing a two-dimensional finite particle model. According to mechanical equations, motion equations and geometric continuity equations. the mechanical parameters of each particle were obtained by temporal difference method. The flying mechanical properties of the rocket explosive device was calculated and discussed combined with test conditions. The results showed that the explosive belt accelerated with rocket dragging and it maintained straight in boost phase. After the explosive belt was dragged out, since the function of the drag parachute, the explosive belt remained at a high level of internal force and it still maintained a straightened state. When the rocket entered the passive section, with the decline of rocket and explosive belt speed, the pulling force of drag parachute to explosive belt failed. So the explosive belt was prone to bend after it crossed the highest point during dropping.