Abstract:
A six-degrees of freedom mathematical model of an experimental
Remotely Piloted Vehicle (RPV) and the linearised longitudinal and
lateral models at 30m/sec are developed.
The longitudinal and lateral dynamics are analysed and the
equivalent discrete systems are used to provide baseline data for the
identification of the aerodynamic derivatives of the RPV.
An advanced aircraft parameter estimation method - the Extended
Kalman Filter - is implemented for the estimation of the aerodynamic
characteristics of the RPV. Conclusions are drawn about the identifiability
of the stability and control derivatives from pitch, roll and
yaw rate measurements.
