Summary

ler? Jason I). ~o l~Q~r~e , ~a r~ R. Morel, lliam S. Levine, and Vero~ica he design, integration, and flight-test development of flight control systems for modern fixed-and rotarywing aircraft constitute a challenging multidisciplinary task that factors significantly in the overall time and cost of aircraft development [ 11. Comprehensive specifications, such as those embodied in ADS-33D (rotorcraft) [2], MIL-STD-1797A (fixed-wing) [3], and MIL-F-9490D (general control system characteristics) [4], and sophisticated time-and frequency-domain evaluation techniques are ap-plied to ensure desired performance and handling qualities and to minimize flight-test tuning of highly augmented modern combat aircraft. The overlap of flexible airframe modes and high-bandwidth control laws drives the requirement for incorporating increasingly higher order analytical and identification-derived simulation models [5] and automated gain selection techniques in the control system design process [6].The control law design and evaluation for a single design point is very laborious because of the numerous (often compet-Mark Tischler (mtischler@mail.arc.nasa.govj is with the