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NASA’s Self-Bootstrapping IPC operates in either transition mode for bootstrapping or fixed frequency mode for a regulated output via closed feedback. The transition mode is initially turned on via the input (i.e., primary) voltage control of the main switch and acts as a bootstrap converter utilizing a Gallium Nitrate transistor to control peak primary inductor current. That peak current can be varied via the sensor gain and/or a precise artificially generated offset and controls the switching frequency together with the secondary load (i.e., output). The IPC operates in transition mode until the Pulse Width Modulator (PWM) Under Voltage Lockout threshold is reached and fixed frequency mode begins. Fixed frequency operation is controlled by the PWM and the normal operation mode of the converter maintains a frequency while varying the duty cycle as needed. The PWM is secondary ground referenced and controls primary switching via galvanic isolation. The peak current in transition mode is set higher than the peak current in fixed frequency operation to prevent interruption or instability while in fixed frequency operation after bootstrap is completed. However, the transition mode control can serve as the overall peak current limiter. This invention is applicable to both flyback and buck-derived topologies with similar efficiency and size advantages. While NASA originally developed the Self-Bootstrapping IPC for CubeSats and space-based electronics with strict SWaP requirements, it may also be useful for safety-critical industries (e.g., aerospace and defense) to allow for high reliability power supplies and more favorable SWaP than existing state-of-the-art high-power dc-dc converters. The reliability, efficiency, and SWaP advantages of this NASA invention could also benefit medium- and high-power commercial power supplies.

Combining a dynamic load emulation technique with a PWM dithering technique, NASA’s technology provides a more efficient, cost-effective, and practical method to emulate complex loads. While there are commercially available electronic device loads on the market that meet basic emulation needs, these devices are limited; they are limited with respect to small input voltage changes, and to feedback signals from the device’s power system, which may lack the strength and resolution needed to emulate accurately. A common solution for the bus emulation limitation is to construct a model of an actual microgrid using representative loads and connections. But this can be complex, costly, and have limitations in performance. NASA’s approach addresses these challenges without creating an actual model microgrid to replicate the systems. As opposed to stand-alone COTS electronic load devices or model microgrids using representative loads and connections for a given test, NASA’s technology is a system constructed of an input power filter, a COTS electronic load device or load subsystem, and a power control circuit. The input power filter is designed to emulate load or bus performance at the medium to high frequency range. The power control circuit combined with the electronic load or load subsystem emulates lower frequency and constant power dynamics of the system. Lastly, the power control circuit linearizes digitization and quantization issues present with digitally controlled COTS electronic loads. The power control circuit can be set to measure a load voltage, which is divided by a determined value for power, and combined with a triangle wave dither (the power control circuit block image demonstrates how to integrate a triangle wave dither). This dither dynamically adjusts the electrical current or power to keep it constant within the commercially purchased load device, enabling accurate emulation of complex DC microgrid systems.