针对翼型橇终点效应试验攻角控制问题,采用基于耦合流场数值模拟方法与刚体六自由度运动方程的被试品飞行攻角工程预示程序,获取了弹-橇分离过程中被试品攻角和特征位置处弹-橇相对位置与飞行时间、距离的关系,分析了地面效应、橇体气流扰动作用下被试品气动力矩变化趋势,研究了预置攻角、分离速度、轨道参数对分离过程中被试品压心位置及攻角变化的影响规律,为翼型橇弹-橇分离方案优化设计提供技术支持。

Under the special configuration the airfoil rocket sled, an engineering prediction code based on the numerical flow simulation method as well as the six degrees of freedom function was used to investigate the angle of attack of missile and the relative missile-sled position in the separation process. The influence on aerodynamic moment of the missile from the ground effect as well as the aerodynamic interference between the missile and sled was studied. In the meanwhile, the influence in the center of pressure and angle of attack of missile from the presetting angle of attack, separation speed and track parameters was studied. The conclusions would point out some technical directions to optimize the missile-sled separation plan for the airfoil rocket sled.