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A compact hydrogen generation device of fuel cell system using chemical hydride storage technique was designed to fit the propulsion device requirement of a small unmanned aerial vehicle(SUAV). For high efficient, compact, and lightweight hydrogen generation control device, the Co-B catalyst hydrogen conversion rate by NaBH4 aqueous solution flux is measured so that the proper amount of Co-B catalyst for maximum hydrogen generation of 100W stack was proposed. A compact hydrogen generation device is controlled by pump's on/off using its own internal pressure and consumes fuel in high efficiency through a dead-end type fuel cell. The fuel cell system has stable operation for a planed flight profile. The system operates up to maximum 7 hours and at least 4 hours for tough flight profiles.

This paper proposes a design method of the position, velocity, and current controller for a hall sensored BLDC motor using TMS320F2812, a velocity estimation algorithm using a hall sensor, and a robust controller design method for an actuator system with uncertainties. The actuator for missiles requires high precision, fast response, and smaller size. The controller of the actuator should also satisfy these requirements. Although the analog controller provide precise control and fast response, the implementation of control algorithm and the modification of controller design are not easy. However, the digital controller solves these difficulties of the analog controller, since it implement the control algorithm as software. Moreover, it is easy to simulate under MATLAB/SIMULINK with the digital controller, which makes the digital controller more preferred.

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