| With the development of astronautics technology, how to improve the reliability of aerocraft navigation systems becomes more and more important. The performance of the gyro, which is the essential part of the inertia navigation system, is crucial to the system. In order to enhance the reliability of both armament systems and space crafts, and also to reduce the risk of systems running, life of gyros must be tested.In this dissertation, an intelligent control system for testing life of dynamic tuned gyros is designed, according to the requirement of intelligentization process. This control system can test and track power supply parameters and running parameters of gyros in four isolated, non-interferential channels simultaneously. Moreover, it can also fulfill many functions, such as collection, display, reading off, communication, reserve and management, etc. continuously without watch. The system has fault mode self-detective ability; when parameters become abnormal, it can dispose the problem automatically based on the fault type, to insure security of the gyros. According to the desired functions of the systems, gyros rebalancing loop, temperature controlling circuit, gyro power supply testing circuit, two-phase electrical current testing circuit, and gyro moment current output testing circuit, have been designed in the hardware part. The main functions of the software part are: simulating parameters collection, controlling relays and parameters display, and the design of data-base.Concerning the noise disturbance along the data collecting process, a digital filter which based on adaptive filter theory has been designed in this dissertation. LMS adaptive algorithm is adopted for the filter. This filter is proved to have fine performance, via software implementation, and through comparison with analysis of other digital filter methods.In the last section, a systematic debugging is done. The test result and some concrete measures for improving system's performance are also given.
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