气动加热参数辨识在型号设计中的应用

Parameter Identification of Pneumatic Heating in Missile Design

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。

To solve the problem of temperature measure in tactics missile flying experiment, the parameter identification of the surface heat transfer for the thermal shield is given by using the temperature measurement of inside points of the thermal shield and introducing the sensitive coefficient in this paper. The nowell posed question of this parameter identification is also solved and the whole pneumatic heating process in flying process is obtained. The experiment result is showed that the error of temperature calculation can be improved by mew method and the design will be improved. This method is valuable in the design for tactics missile.