This paper considers the effect of choice of actuator technology and associated power systems architecture on the mass cost of implementing active flow control systems on civil transport aircraft. The research method is based on the use of a simple systems mass model that includes a mass term due to systems hardware and a mass term due to the system energy usage. An A320 aircraft is used as a case study application. The mass model parameters are based on first principles physical analysis of electric, pneumatic and hydraulic power systems combined with empirical data on system hardware from existing equipment suppliers. Flow control actuator technologies include pneumatic, electromechanical-fluidic and electro-hydrodynamic. It is shown that the actuator power generation and distribution systems form the greatest part of the system mass cost. The power specific mass of electrical power distribution is shown to be considerably less than that for pneumatic systems, however this advantage is reduced by the requirement for relatively heavy electrical power management and conversion systems. A trade exists between system power efficiency and the system hardware mass required to achieve this efficiency. For short duration operation the solution is driven towards lighter, less power efficient systems, whereas for long duration operation there is benefit in considering heavier but more efficient systems. For the A320 application it is shown that engine bleed based pneumatic systems are less efficient and practical than solutions that use electrical power offtake from the engine to either drive a centralised air compressor or to power distributed electromechanical-fluidic actuators. Leading edge separation control systems require greater power than trailing edge systems due to the difference in local velocity. It is estimated that a practical electromechanical-fluid flow control system may have a mass of up to 40% of slat mass for a leading edge application and 5% of flap mass for a trailing edge application.
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