Determining Aircraft Moments of Inertia from Flight Test Data

Flight test maneuvers and dynamic modeling techniques were developed for determining aircraft moments of inertia from flight test data. Full nonlinear rigid-body rotational equations of motion were used in the analysis, with aerodynamic moment dependencies modeled by linear expansions in the aircraft states and controls. Aerodynamic parameters were estimated simultaneously with inertia parameters using equation-error modeling applied to flight test data from maneuvers designed specifically for this problem. The approach was demonstrated using a nonlinear F-16 simulation, then applied to a remotely piloted subscale aircraft flight test. Errors in the aircraft moment of inertia parameters determined from simulated F-16 flight test data were less than 6% compared to the true values in the simulation. Flight test results for the subscale aircraft were within 6% of ground-test values obtained using the same aircraft.

Automated summary

Flight test maneuvers and dynamic modeling techniques were used to determine aircraft moments of inertia, with aerodynamic moment dependencies modeled by linear expansions. Aerodynamic and inertia parameters were estimated simultaneously using equation-error modeling, with errors less than 6% in simulated F-16 flight test data. Results from the subscale aircraft flight test were within 6% of ground-test values.