Application of parameter estimation to highly unstable aircraftThis paper discusses the application of parameter estimation to highly unstable aircraft. It includes a discussion of the problems in applying the output error method to such aircraft and demonstrates that the filter error method eliminates these problems. The paper shows that the maximum likelihood estimator with no process noise does not reduce to the output error method when the system is unstable. It also proposes and demonstrates an ad hoc method that is similar in form to the filter error method, but applicable to nonlinear problems. Flight data from the X-29 forward-swept-wing demonstrator is used to illustrate the problems and methods discussed.
Document ID
19860062917
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maine, R. E. (NASA Flight Research Center Edwards, CA, United States)
Murray, J. E. (NASA Flight Research Center Edwards, CA, United States)