The F/A-18's flight control system (FCS) is highly augmented to tailor flying qualities, increase departure resistance, and help protect the airframe structure throughout the flight envelope. Since the F/A-18 flight control laws were designed primarily for the symmetrically loaded airplane, the effects of high lateral asymmetries represent a significant off-design condition where control margins may be substantially reduced. Adequately defining the flight envelope limits requires a flight test program that addresses the stability and control, structural, and mission suitability issues associated with these large lateral weight asymmetries. This paper will address the risk reduction techniques, test methodologies, and real-time analysis tools that have been used in the past or are planned to be used in an ongoing flight test program to expand the lateral asymmetry limits of the F/A-18.
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