The Stanford relativity gyroscope experiment flight gyro suspension system

In this paper the author describes work on the simulation of a suspension system for levitation and precision positioning of the niobium coated spherical quartz gyro rotor during orbital flight. The system employs multiple controllers and estimators with microprocessor (Z80) controlled range switching. The resulting system handles external accelerations up to 1 g in the highest range, yet in the lowest range, below 10-6 g, the sensor noise power spectral density produces only 10- 10 g rms in the rotor. The system is capable of automatic emergency switch up within 100 μsec. Switch down is automatic to expected flight levels of x 10- 8 g. Positioning accuracy in all ranges including emergency switch up is μin static and ± 50 μin dynamic. The average acceleration during the mission should be 10- 10 g to attain the science data accuracy goal. The simulation results to date demonstrate the feasibility of the multilevel flight suspension system as well as the great advantage of operation under dedicated microprocessor control