Flight test experience with an adaptive control system using a maximum likelihood parameter estimation techniqueThe flight test performance of an adaptive control system for the F-8 DFBW aircraft is summarized. The adaptive system is based on explicit identification of surface effectiveness parameters which are used for gain scheduling in a command augmentation system. Performance of this control law under various design parameter variations is presented. These include variations in test signal level, sample rate, and identification channel structure. Flight performance closely matches analysis and simulation predictions from previous references.
Document ID
19790061344
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Hartmann, G. (Honeywell, Inc. Minneapolis, MN, United States)
Stein, G. (Honeywell, Inc. Minneapolis, Minn., United States)
Powers, B. (NASA Flight Research Center Edwards AFB, Calif., United States)