喷咀轴向位置对复合增程弹气动特性的影响

The Effect of Axial Position of Nozzle on Aerodynamic Characteristics of Hybrid Extended Range Projectile

底排-火箭复合增程弹分置式布局,即底排装置设置在弹底,火箭助推装置设置在弹丸前端的弧形段部分,是一种特别适合于子母弹的先进布局方式。文中对火箭喷咀轴向位置的变化对分置式结构底排-火箭复合增程弹气动特性影响进行了风洞实验研究。实验Ma数为2.0和3.0,迎角为0°～6°,喷流压力比为0～189.6,喷流介质为冷空气,喷咀倾角30°,喷咀数量4个,喷咀轴向位置有三种,分别位于弹丸肩部、头部弧形段和圆柱部。实验研究结果表明:喷流后喷咀轴向位置位于弹丸肩部时弹丸阻力系数和俯仰力矩系数下降幅度最大,而升力系数及压心系数增加幅度最大,底阻增加幅度最小,是最有利于飞行的一种布局方式。

The hybrid base-bleed-rocket extended range projectile is an advanced layout for cluster bomb when it adopts independent layout that the base bleed device is installed on the projectile base and the rocket roll booster is installed on the ogive of projectile head. This type of layout fits cluster bomb in particular. In this paper, how the axial position of the rocket nozzle effects the aerodynamic characteristics of hybrid base-bleed-rocket extended range projectile was investigated through wind tunnel test study. Experimental Mach numbers are 2.0 and 3.0 respectively, the angle of attack range ranges from 0 to ＋ 6 degrees, and jet pressure ratio range ranges from 0 to 189.6. The media of jet is cool air, and the inclined angle of nozzle is 30 degrees. The number of nozzle is four. There are three types of axial position of nozzle, which are respectively the projectile shoulder, the projectile arch and the cylinder section of projectile. Experimental results show that the decrease of the drag coefficient and the pitching moment coefficient are maximal, the increase of the lift coefficient and the pressure center coefficient are maximal, and the increase of the base drag coefficient is minimal, when tile axial position of nozzle is the projectile shoulder. This type of layout is the most favorable one for flight.