All-electric aircraft is a high priority goal in the avionics community. Both increased reliability and efficiency are the promised implications of this move. But, thermal management has become a significant issue that must be resolved before reaching this goal. Advanced analysis technologies such as finite element method and intelligent control systems such as field oriented control are being used to better understand the source of the heat and to eliminate as much of it as possible. This paper addresses the motivation behind allelectric aircraft and gives an overview of some of the considerations in cooling, simulation and modeling, and control, with an example of one control scheme which is being developed.= maximum allowable current change rate

A proposed method for accommodating hightemperature operation has been studied and developed through combined efforts of Advanced Power Electronics Corporation (ApECOR) and University of Central Florida. A novel process is being explored that will ultimately lead to design, fabrication, and verification of high temperature packaging for silicon carbide (SiC) power modules. The process is established to advance the operational capabilities of power modules during hightemperature conditions. Prototype modules were produced and underwent significant testing to establish capability of operation at a minimum temperature of 350 • C with probable expectation of operation in excess of 400 • C. A strenuous thermal cycle testing apparatus was established to rapidly cycle prototype modules between 80 • C and 350 • C in excess of 150 iterations per module. Analysis of the testing data did not exhibit degradation in the module performance characteristics, indicating successful module design performance. Based on the scope and goals of this research effort, further development of the design process is believed to be feasible for progression towards further development and commercialization.

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The development of electromechanical actuators (EMAs) is the key technology to build an all-electric aircraft. One of the greatest hurdles to replacing all hydraulic actuators on an aircraft with EMAs is the acquisition, transport and rejection of waste heat generated within the EMAs. The absence of hydraulic fluids removes an attractive and effective means of acquiring and transporting the heat. To address thermal management under limited cooling options, accurate spatial and temporal information on heat generation must be obtained and carefully monitored. This model can also be incorporated into lumped node magnetic and electric model to develop a full multi-physics, multi-scale simulation engine. This engine can accurately analyze the complete EMA system in a systematic scale and whole-mission duration.

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