A fuel control system is being designed and developed for a new aero engine of afighter aircraft. But existing facility doesn’t support the full operational testing of theindividual components of aircraft fuel control system under various aircraft accelerationconditions.In this paper theoretical analysis has been done to check the flow distribution ofone of the basic systems i.e. Main Engine Control Unit (MECU) under various aircraftaccelerations. It has been observed that, in normal mode upon application of verticalorientated acceleration, for the flow rate of 1572 gph from the pump, a maximumvariation of 0.17% in the combustion chamber flow rate has been observed. For this casea maximum variation of 3.3% in pressure (at Upstream MPV) was also observed. Thesevariations are within permissible limit of variations that can be sustained by MECUcircuit. In case of manual mode there is a large offset between experimental andsimulation results (as large as 10 percent) but effect of possible ‘g’ effect is within 2percent of the base results. Moreover, effect of sustained acceleration effect of ‘5g’ for5minutes has also been analyzed and both the configuration and performance parametersare almost the same as the regular aircraft acceleration. It has also been analyzed thatEmergency Spill Valve (ESV) and Pump Pressure Relief Valve(PPRV) which are springloaded will not be falsely activated under operational ‘g’ effect. Key words: Aircraft acceleration, falsely activated, Main Engine control Unit (MECU),Sustained Acceleration
