Experimental Testing and Validation of the Mathematical Model for a Self-Humidifying PEM Fuel Cell

Abstract

This paper presents an experimental testing and validation results for a zero-dimensional self-humidifying PEM (Proton Exchange Membrane) fuel cell stack. The model incorporates major electric and thermodynamic variables and parameters involved in the operation of the PEM fuel cell under different operational conditions. The mathematical equations are modelled by using Matlab-Simulink tools in order to simulate the operation of the developed model with a commercially available 1 kW Horizon (H-1000) PEM fuel cell stack, which is used for the purposes of model validation and tuning of the developed model. The model is mathematically modelled and presented in the recent published work of authors. The observations from model simulations provide sufficient evidence and support to the results and observations obtained from testing 1 kW Horizon (H-1000) PEM fuel cell stack used in this research. The developed model can be used as a generic model and simulation platform for a self-humidifying PEM fuel cell with an output power varying from 50 W to 1 kW, with extrapolation to higher powers is also possible.

Pressure Vessel Mass Estimation for High Altitude PEM Unmanned Aircraft System

“…Based on the flow rates of supply hydrogen and air for the Horizon (H-1000) fuel cell stack, as presented in the previous published research work [16], and presented in Appendix A, Table A.1, at 20 A current and power of 990 W, the flow of supplied air is 1.766 m 3 /min (105.96 m 3 /hour), and the flow of supplied hydrogen is 11.85 L/min (0.711 m 3 /hour or 0.064 kg/hour). Based on the developed model of the PEM fuel cell stack of 72 cells as presented in [14,17] at 20 A current and power of 877 W, the flow of supplied air is 97.9162 m 3 /hour, and the flow of supplied hydrogen is 0.6368 m 3 /hour. Where, at standard temperature and pressure, the density of dry air is 1.225 kg/m 3 , the density of oxygen is 1.429 kg/m 3 , the ratio of oxygen to air is 21%, and the density of hydrogen is 0.0899 kg/m 3 .…”

“…The stainless-steel materials are chosen based on their specifications in offering high yield strength, high stress resistance, high corrosion resistance, and their availability in a decent range of thicknesses, also their suitability in storing high pressurised gases for aerospace and industrial applications. However, all calculations related to the design of pressure vessels and power-plant mass estimations in the following sections of this research will be determined based on the developed model of the PEM fuel cell stack in [14,17], and the proposed equations (3, 5, 6, 9, 10, 11, 12, and 15) above.…”

“…ratio of oxygen to air is 21%), therefore, the design or air vessel will be excluded in this research. At sea level, based on the developed model of a PEM fuel cell stack in [14,17], for one hour's operation of the stack at (maximum current of 20 A and power of 877 W), the required supply of pure oxygen is 20.5624 m 3 /hour under 1atm ambient pressure. Using Eq.…”

Design of an unmanned aircraft system for high-altitude 1 kW fuel cell power system

“…Gudmundsson [23] claimed that efficiency of the propeller varies throughout the different phases of the aircraft's flight. Saleh et al [24,25] claimed that for a 1 kW PEM fuel cell, Horizon operates at a maximum output of 877 W with a current rating of 20 A, achieving 87.7% efficiency. Therefore, in this research, the propeller efficiency is assumed to be 80%.…”

“…The assumptions for constraint calculations for the UAS power by a 1 kW PEM fuel cell system are as given in Table 7, by substituting the values of Table 7 in Eqs. (22)(23)(24)(25)(26)(27) to determine the relation between thrust-toweight ratio T/W and the wing loading W/S of the design as presented in Fig. 6.…”