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针对战术导弹飞行试验的温度实测问题,通过测量弹体表面的温度,引入敏感系数,提出弹体表面气动加热热流的参数辨识方法。解决了该参数辨识定解问题的不适定性,从而获得导弹飞行全程的气动加热热流信息。飞行试验表明,通过参数辨识可获得较现有气动加热计算方法更为精确的结果,能提高设计的准确度。该计算方法在导弹设计中有较大的应用价值。
In order to solve the problem of temperature measurement in the tactical missile flight test, the parameter identification method of the aerodynamic heating heat flow on the surface of the projectile is proposed by measuring the temperature of the projectile surface and introducing the sensitivity coefficient. The ill-posed problem of the parameter identification is solved, and the information of the aerodynamic heating heat flow of the missile flight is obtained. Flight tests show that more accurate results than existing aerodynamic heating methods can be obtained through parameter identification, which can improve the design accuracy. The calculation method has great application value in missile design.