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Next generation aircraft will require more electrical power, more thermal cooling, and better versatility. To attain these improvements, technologies will need to be integrated and optimized at a system level. The complexity of these integrated systems will thus be increased and will require considerable analysis. In order to characterize and understand the implications of highly integrated aircraft systems, the effects of pulsed power, highly transient loads, and the technologies that drive system stability and behavior, an approach will be taken utilizing integrated modeling and simulation with Hardware-in-the-loop (HIL). Such experiments can save time and cost and increase the general understanding of electrical and thermal phenomena as it pertains to aircraft systems before completing an integrated ground demonstration. A dynamometer “drive stand” was characterized to ensure its drive performance can match that of a fighter class turbofan jet engine. Simulation tests were performed by applying various electrical loading profiles to a Low Spool generator characterizing its stability and operating margin. Hardware and software results were verified against each other and the impact to power quality and system stability and control was demonstrated at various mission conditions.