Aerodynamic data fusion technique exploration
Chen Yan-qin · Kongqi donglixue xuebao · 2009
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.