experiment schedule and/or the load model forecast. If the error is not excessive, only the mathematical load model parameters are updated for each dynamic load. The relay setting control system determines which relay system should be operational and what the relay setting should be for the present configuration and system loading. The configuration monitor determines the potential future operating modes, the expected equipment loading for the power system and the most likely system configuration. Since this function is an intimate component of the relay setting control system, it will be included within that function for the remaining sections of this paper. Normally, the configuration monitor is used for other network analysis functions. The instrumentation model parameter update uses the estimated system state to determine the conversion curve changes for all measurements. As the instrumentation equipment ages, the conversion of metered value to actual units will change. Hardware Implementation The proposed hardware system to implement the above functions is shown in Fig. 3. The instrumentation would be located at key points on the spacecraft power system and interconnected with the SCADA microprocessor through a high-speed redundant communication network. The SCADA microprocessor would be connected to the SEBMD microprocessor through a high-speed databus. The SEBM microprocessor would be connected to the RSCS, the IMPU and the SDPU microprocessors through high speed databuses. The relay systems would be located at key points on the spacecraft power system and interconnected with the RSCS microprocessor through a high-speed redundant communication network. If the high speed databuses were implemented as a fault tolerant network databus, then it would be possible to implement this design as a distributed control system of dedicated microprocessors and embedded controllers. This type of distributed control system should yield the highest level of redundancy. The estimated computer requirements are based on the assumption that the spacecraft power system is composed of 30 nodes, 60 distribution lines, 4 power sources, 100 loads and 600 relay systems. Based on personal computer-system resource capability (e.g. IBM PS/2 Model 50), it is estimated that the SCADA system should
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