Detection and Isolation of Instrumentation Failures Applied to GPS and Inertial Navigation

摘要

During flight tests and during post-processing of flight data, a need exists to validate that all sensors are working properly and that data is valid after experimentation. Analytic redundancy methods enable data validation using multiple, dissimilar instruments processed through the vehicle dynamic system model. A design methodology is presented through which the designer chooses the instrumentation for flight test using output separability of the failure modes as the design metric for measuring system integrity. An example is presented using an aircraft navigation system.