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DIGITAL VALVE CONTROLLER SYSTEM FOR CONTROLLING WATER FLOW. THE SYSTEM CONTINUOUSLY CONTROLS THE PRESSURE OF WATER GOING INTO A METER AREA OR PRESSURE MANAGED ZONE. THE SYSTEM CONSISTS OF A CONTROLLER, REMOTELY CONTROLLED VALVES AND REMOTE DIGITAL SENSORS CONNECTED TO A SERVER WHICH PERFORM DEVICE COMMUNICATION, ALARM PROCESSING, HOSTING SYSTEM CONTROL INTERFACE, DATA PROCESSING AND STORAGE, SYSTEM OPTIMISATION AND CLIENT DATA SYSTEM INTERFACE.

A COMBINED ELECTRONIC CONDUCTIVITY METER, PH METER, THERMOMETER, FLOWMETER, RELAY AND FLOW SWITCH FOR USE IN COOLING TOWERS. INFORMATION CAN BE EXTRACTED BY USB MEMORY STICK.

CURRENT MONITORING PULSED DC CONTROLLER, BRINGS TOGETHER POWERFUL LONG-RANGE IONISATION; CLOSED-LOOP FEEDBACK; SELF-MONITORING AND REMOTE REPORTING. A COMPLETE PACKAGE, SELF-MONITORING AND ADJUSTMENT OF PERFORMANCE ALLOWS OPTIMUM CONTROL OF STATIC FOR MUCH LONGER PERIODS THAN PREVIOUSLY POSSIBLE. LOCAL DISPLAY AND OUTPUT SIGNALS ALERT OPERATORS TO THE NEED TO CLEAN THE EQUIPMENT.

A GENERATOR CONTROL UNIT (GCU), USED TO MONITOR AND CONTROL THE INTEGRATED DRIVE GENERATORS WHEN THEY ARE POWERING AIRCRAFT LOAD BUSES. IT HAS TWO MAIN AIRCRAFT TASKS: CONTROL AND PROTECTION; TO MONITOR AND CONTROL THE QUALITY OF ELECTRIC POWER SUPPLIED TO THE AIRCRAFT AND BUILT-IN TEST EQUIPMENT (BITE); TO COLLECT AND ANALYSE FAULT DATA AND SAVE THIS FOR LATER RETRIEVAL BY MAINTENANCE PERSONNEL.

PROBE HEAT COMPUTER (PHC), USED IN CONJUNCTION WITH AN AIRCRAFT ANTI-ICING SYSTEM OF PROBES AND SENSORS. THE PHC IS A RECTANGULAR UNIT WHICH HAS A BOX ASSEMBLY WITH PRINTED CIRCUIT BOARDS. THE CPU PERMANENTLY MONITORS THE PROBE ANTI-ICING OPERATION. THE PHC PROVIDES AN ANTI-ICING FUNCTION WITH DATA PROCESSING. THE FUNCTIONS INCLUDE: POWER SUPPLY, ANTI ICING OF THE TOTAL PRESSURE PROBE, OUTER AIR TEMPERATURE SENSOR, ANGLE OF ATTACK SENSOR AND RIGHT/LEFT STATIC PRESSURE PROBE. IT PROVIDES POWER SUPPLY CONTROL AND SUPPLIES RELATED WARNING SIGNALS.