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<title>AAS 98-179</title><body BGCOLOR="ffffff"> <h2>AAS 98-179</h2> <h2>STUDY OF SENSOR REDUNDANCY AND EFFECT OF ACCELEROMETER FOR FLEXIBLE EXPENDABLE LAUNCH VEHICLES (ELV)</h2> <h4>Zhaozhi Tan, P. M. Bainum - Howard University</h4> <h2> Abstract </h2> A simplified mathematical model of an expendable launch vehicle system suitable for subsequent control design has been established. It was requested by our grant sponsor that we consider an accelerometer collocated with the position gyro to be added to the system as an additional sensor. According to requirements of the grant sponsor the problem of sensor redundancy is also studied. The simulation results are given for comparison of the situations where: (1) none of the gyros, (2) one, or (3) two gyros fail. The effect of including (or deleting) the accelerometer as an additional sensor is also studied. <P><A HREF="http://www.space-flight.org/AAS_meetings/1998_winter/sessions.html">Back</A>