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干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 aerodynamic characteristics of supersonic canard-controlled sounding-rockets were studied by wind tunnel test.Aerodynamic force and moment of different rocket models including the body,canard wings,rolling tails and fixed tails were compared and analyzed from-8 to 10 attack angles under Mach number 1.5 and 3.0.The result proves the different effect on aerodynamic force and moment of different parts of the rocket.The efficiency of rolling control of rolling tail is higher than the fixed tail.The problem of losing efficacy of canard rolling control nearby transonic speed was solved by using rolling tails.The efficiency of the pitching control is not closely related to the rolling or fixed tail.The result is useful for the design of the canard-controlled sounding rockets.
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