Logic changes on the data bus, address bus, and control lines of the microprocessors.
To develop design and integration methods for fault tolerance and functional integrity in complex and highly integrated flight critical systems. The motivation for this research is the increasing trend in advanced aircraft designs to require onboard computers to perform flight-critical functions. The problem of verifying the integrity of control computers in adverse, as well as nominal operating environments is a key issue in the development and certification of critical control systems. Electromagnetic fields may couple directly into computer systems through breaches in the shielding or may cause analog electrical transients to be induced on the aircraft's wiring. These signals can propagate to the onboard electronic equipment and result in a common-mode functional failure or upset of multiple processors in the control computers that affect performance and reliability.