基于数学模型的气动力数据融合研究

Aerodynamic data fusion technique exploration

气动力误差来源复杂,气动力真值通常未知,气动力误差传递数学模型的建立非常困难,因此直接将信息融合技术应用于气动力数据融合目前还不可行。迄今为止,未见气动力数据融合的公开报道。本文首次提出了基于数学模型的气动力数据融合准则和方法。首先建立反映气动数据变化规律的数学模型,然后基于气动力数学模型,根据无论计算数据、风洞实验数据、还是飞行试验数据都必须满足气动力变化规律的原则,以气动力数据满足气动力变化规律的程度为依据,建立气动力数据融合准则和融合方法。算例表明,所建立的融合准则和方法是可行的。

Aerodynamic error source is complex, aerodynamic true value is usually unknown, and the mathematic model of aerodynamic error transition is difficult to constructed, so information fusion technique can not be directly used in aerodynamic data fusion at present time. So far, It is doubtful whether there is any published paper about aerodynamic data fusion. Aerodynamic data fusion criterion and method presented in this paper may be the first time. At first, mathematic model reflecting aerodynamic variation law is constructed, according to the rule which computation data and wind-tunnel test data and flight test data must satisfy aerodynamic variation law, and based on the degree of which kind of aerodynamic data satisfy the aerodynamic variation law, then aerodynamic data fusion criterion and method is constructed. Examples show that the aerodynamic data fusion criterion and method are feasible.