Phase variable transformations are used to construct the mathematical model of an aeroelastic aircraft in a form that is amenable to partial or piecemeal acceptance of parameters estimated from flight data. The problem is one of parameter identification of large scale dynamic systems involving a system matrix characterized by about 200 elements. A mathematical model of the USAF Total In-Flight Simulator was computed using the FLEXSTAB program. As data became available during the progress of the flight test program, it was processed and substituted in the mathematical model for parameters obtained from the FLEXSTAB program. Results tend to show a progressive and orderly transition from an analytically defined mathematical model to one obtained from the flight tests of the actual aircraft.
Identification of the stability parameters of an aeroelastic airplane
Atmospheric Flight Mechanics Conference ; 1978 ; Palo Alto, CA
1978-01-01
Miscellaneous
No indication
English
Aeroelastic problems of airplane design
Engineering Index Backfile | 1956
|Aeroelastic Problems of Airplane Design
NTIS | 1956
|Aeroelastic problems of airplane design
TIBKAT | 1956
|