Dependence of Dynamic Modeling Accuracy on Sensor Measurements, Mass Properties, and Aircraft Geometry

The NASA Generic Transport Model (GTM) nonlinear simulation was used to investigate the effects of errors in sensor
measurements, mass properties, and aircraft geometry on the accuracy of identified parameters in mathematical models
describing the flight dynamics and determined from flight data. Measurements from a typical flight condition and system
identification maneuver were systematically and progressively deteriorated by introducing noise, resolution errors, and bias
errors. The data were then used to estimate nondimensional stability and control derivatives within a Monte Carlo simulation.
Based on these results, recommendations are provided for maximum allowable errors in sensor measurements, mass
properties, and aircraft geometry to achieve desired levels of dynamic modeling accuracy. Results using additional flight
conditions and parameter estimation methods, as well as a nonlinear flight simulation of the General Dynamics F-16 aircraft,
were compared with these recommendations