为了研究气动效应对火箭弹折叠翼展开特性的影响,采用数值模拟方法研究了低速条件下横向折叠翼的气动特性,并对其展开运动过程进行了仿真。计算结果表明,折叠翼所受气动力随着攻角的增大均线性增大,随展开角度的增大表现出先增大后减小的变化规律,且背风侧气动力均小于迎风侧。在负攻角情况下,迎风侧折叠翼展开所需时间长于背风侧,随着风速、攻角的增大,折叠翼展开的同步性进一步减弱。

To investigate the effects of the aerodynamic moment on the folding-wing deployment characteristic, the aerodynamic characteristic and the folding-wing deployment process were simulated. The results show that the aerodynamic forces on the folding-wing increase with the attack angle. The normal force and torque on the leeward folding-wing is smaller than that on the windward folding-wing at a≥0°. The torque on the folding-wing increases firstly and then decreases with increasing of the folding angle. The folding-wing deployment processes of the leeward and windward folding-wing are different and the folding time of the windward folding-wing is longer than that of the leeward folding-wing. The deployment synchronism will be weakened with the increasing of flying velocity and the attack angle.