This paper introduces several new concepts for improving the peak electrical power capability of an aircraft. This capability is becoming very important for the development of future electric power systems and is reflected in the Honeywell more electric architecture (MEA) design concept and energy optimized aircraft (EOA) initiative.
There are many system benefits of using electrically driven actuators on aircraft rather than those that are hydraulically driven. These benefits include enhanced reliability, lower weight, lower volume, and lower cost. However, the introduction of electromechanical actuation (EMA) and electro-hydrostatic actuation (EHA) into aircraft systems has increased the needs for peak electrical power demand.
This paper discusses the concept of aircraft electric power systems in which peak power is increased based on aircraft utilization of existing power sources rather than on an increased power rating of existing components or the addition of new components or systems. This paper also discusses enhancement of load regeneration capability, along with some failure modes and related fault-mitigation provisions. To verify the feasibility of potential systems, a series of computer simulation programs has been developed for different operating conditions. For that reason, simulation results are presented and analyzed. Although implementation of the concept is possible both for alternating current (ac) and direct current (dc) distribution busses, this paper concentrate primarily on dc buses. Examples of existing aircraft electrical power systems that are promising candidates for this approach are shown. Finally, the advantages of these novel system concepts are summarized and conclusions presented.