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采用风洞实验的方法对超音速鸭式布局探空火箭气动特性进行了研究。在马赫数为1.5和3.0、攻角为-8°~+10°的实验条件下,分别进行了箭身、鸭舵、固定尾翼、滚转尾翼的火箭模型组拆实验,并对各模型状态下的气动力和气动力矩特性进行了对比。实验表明,各组件(箭身、鸭舵、尾翼)对全箭气动力和气动力矩的贡献各有不同,滚转尾翼状态的滚转舵效明显大于固定尾翼状态并解决了跨音速附近固定尾翼滚转舵效反效的问题,尾翼滚转与否对鸭舵的俯仰舵效影响不大。实验结果对鸭式布局探空火箭的设计具有一定的参考意义。
The wind tunnel experiment was used to study the aerodynamic characteristics of sounding rockets with supersonic ducks layout. Under the experimental conditions of Mach number of 1.5 and 3.0 and angle of attack of -8 ° ~ + 10 ° respectively, the rocket model grouping experiment with arrow body, duck rudder, fixed tail wing and rolling tail was conducted respectively. Under the aerodynamic and aerodynamic torque characteristics were compared. Experiments show that each component (arrow body, duck rudder, tail) contributes to the total aerodynamic and aerodynamic torque of the whole. The roll-to-run rudder efficiency of the roll-tail condition is obviously larger than that of the fixed tail condition and solves the problem of the fixed tail Rudder effect invalid, tail roll or not on the rudder pitch rudder effect little effect. The experimental results have certain reference meaning for the design of the duck type sounding rockets.