【作者】 屈贤琳；

【导师】 陈少松； 谭献忠；

【作者基本信息】 南京理工大学 ， 工程力学， 2010， 硕士

【摘要】 本文从气动力角度对鸭式布局弹箭进行了研究。理论分析鸭式布局弹箭滑翔飞行中可能引起侧偏的原因有：鸭舵组合打舵条件不理想造成的侧偏和不对称下洗流作用于尾翼造成的侧偏。通过风洞实验得到了无舵模型和三种不同打舵方式带舵模型的气动力数据,通过对不同模型数据的交叉对比分析,研究了各种模型的阻力、升力、俯仰力矩、滚转力矩、偏航力矩、侧向力等气动参数随马赫数、攻角、舵偏角、滚转角等参数变化的规律和异同,并初步探讨了下洗流对弹体造成侧偏的规律与特点。实验结果表明,四种模型的阻力、升力、俯仰力矩系数基本遵循相同的变化机理和规律。四号模型的滚转力矩系数变化比其他三种模型更加剧烈,当弹体处于相对于竖直平面不对称的姿态时,随着攻角增大,下洗流的不对称性愈发显露出来,滚转力矩系数急剧增大,这一现象解释了为什么弹箭在实际飞行中时有转速不均的情况发生。侧向力和偏航力矩系数在有舵时明显大于无舵模型,随攻角和舵偏角的增大,不对称下洗流对侧偏的影响越明显,侧向力和偏航力矩系数增大；侧向力和偏航力矩系数随滚转角的变化呈弦性变化,当弹体滚转到左右对称的姿态时,侧偏值很小,都在零值附近变化,当弹体滚转到左右不对称的姿态时,侧偏值出现明显上下波动。更多还原

【Abstract】 In this dissertation, canard configuration missiles are studied from the view of aerodynamic. First, the reasons which cause the conrnerning of rolling flight of canard configuration missiles may have two. One is that the cornerning is caused by the non-ideal conditions of rudder swinging, and the other one is that the cornerning is caused by the asymmetric downwash flow acting on the empennage. By the way of wind tunnel experiment, we got aerodynamic data of non-rudder model and other three kinds of models. According to the experimental results of different kinds of models, we got the variation regularity of resistance, lift force, pitching moment, rolling moment, yawing moment and yawing force of the models which vary with Mach number, attack angle, elevator angle and roll angle. By crossed comparative analysising the data of different kind of models, investigate similarities and differences of the aerodynamic characteristics of each kind of model, and analysis the regularity and characteristic of cornering which is caused by the asymmetric downwash flow.Experimental results showed that, the four kinds of modes have the same variation mechanism and regularity in resistance, lift and pitching moment. Number 4 model vary moer violently with attack angle than other three kinds of models. When the missile body is on asymmetric posture of the vertical plane, with attack angle increasing, asymmetry of downwash flow show up more obviously, and rolling moment coefficient raise rapidly. This situation explains that why the missiles in actual flight have the phenomenon that rotation speed is uneven. Lateral force and yawing moment of the models with rudders are obviously bigger than the ones without rudders. With the attack angle and elevator angle raising, the influence asymmetric downwash flow acting on cornerning becomes harder, lateral force and yawing moment increase. Lateral force and yawing moment vary in sine or cosine when roll angle change. When the missile body is on symmetric posture, the values about cornerning are small and vary around zero. When the missile body is on asymmetric posture, the values about cornerning show obviously fluctuation.更多还原