Search Results

This paper presents an overview of electric secondary power system configurations for future military and commercial aircraft. The overview includes a description of the salient elements of each configuration, as well as a comparative assessment of the near-term application risks. Configurations range from conventional 115 V, 3 phase, 400 Hz to engine integrated 270 Vdc systems. The Defense Systems Management College, Ft. Belvoir, VA methodology is used for risk assessment. The elements of risk for each configuration are identified and quantified to indicate areas of technical development in support of risk reduction. The selected configurations are in keeping with those being actively pursued by the TriService/NASA Joint Planning Team (JPT) for More-Electric Aircraft (MEA), headed by the USAF Wright Laboratories (WL).

Traditionally, aircraft systems have relied upon bleed air from the main engine as the primary energy source for environmental control systems (ECS) and anti-icing systems. With the next generation of engines, bleed air may not be available to the extent utilized in the past. Electric drive systems are now being considered as viable alternatives for ECS. Electric drives are also being considered for traditional hydraulic drives in applications such as engine fuel pumps, and flap actuators. Several aspects of electric drive systems consisting of permanent-magnet motors (PMM's) and solid-state power electronics for the primary generation or secondary control of electric drives on aircraft are discussed in this paper. For power distribution, conventional 120/208-v, 3-phase, 400-Hz; 270-vdc, variable frequency/constant voltage, and variable frequency/variable voltage systems are the primary candidates.