<div class="section abstract"><div class="htmlview paragraph">Aircraft electrification is one of technological innovations to achieve the goal
of CO<sub>2</sub> emission reduction in civil aviation. In present research, we
focus ourselves on an Electric Fuel Metering System (EFMS). Aircraft systems are
commonly expected to make not only simplified configuration and improvement of
controllability, but also safety and reliability. The electrification of fuel
system also requires the similar approach. Therefore, a simple and reliable
redundancy concept is a crucial challenge. In addition, stable and responsive
controllability that does not affect engine operation is required, especially in
fuel system, it is desired to achieve both accurate metering and short settling
time without overshoot or undershoot. However, in such a system, the response is
nonlinear due to the fuel flow circuit and the motor drive during current
limiting. Systemizing a control design that takes these constraints into
considerations and that satisfies the requirements over a large dynamic range,
has not been discussed. This paper discusses a design methodology to achieve
optimal fuel flow control in the EFMS with redundant electric fuel pumps,
considering motor current limitation by current limiters. The flow control model
is created by adding the flow command increment limiter estimated as equivalent
to the current limiter. Using this model, the gain characteristic map is derived
analytically. The control system is extended to an active-active control
redundant system. The compensating action of that system ensures that if one of
the fuel pumps suddenly shut down, the remaining fuel pumps will autonomously
increase their flows to maintain the required flow for the engine fuel burn.</div></div>