Abstract: In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.

Abstract: An air compression system for a fuel cell system, the air compression system has a main air compressor with a maximum air flow output approximately equal to a continuous mode air flow requirement of the fuel cell system. The main air compressor weighs less than an air compressor having a maximum air flow output approximately equal to a peak air flow requirement of the fuel cell system such that the weight of the air compression system is reduced compared to a conventional air compression system. The air compression system also includes a supplemental oxygen supply system which is fluidically coupled with the fuel cell system.

Abstract: In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.

Abstract: Recognizing the fact of extremely low utilization of peak power (especially in the aviation use case), we propose a novel approach to significantly reduce the size and weight of the system by downsizing the main air compressor to match the air flow required to produce the desired continuous power (e.g., 55% of the peak power rating for the aviation applications, etc.), and provide the supplemental oxygen flow from an on-board high-pressure oxygen tank.

Abstract: In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power spikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.

Abstract: Recognizing the fact of extremely low utilization of peak power (especially in the aviation use case), we propose a novel approach to significantly reduce the size and weight of the system by downsizing the main air compressor to match the air flow required to produce the desired continuous power (e.g., 55% of the peak power rating for the aviation applications, etc.), and provide the supplemental oxygen flow from an on-board high-pressure oxygen tank.

Abstract: Recognizing the fact of extremely low utilization of peak power (especially in the aviation use case), we propose a novel approach to significantly reduce the size and weight of the system by downsizing the main air compressor to match the air flow required to produce the desired continuous power (e.g., 55% of the peak power rating for the aviation applications, etc), and provide the supplemental oxygen flow from an on-board high-pressure oxygen tank.

Abstract: In one or more embodiments of the novel aircraft fuel cell system without the use of a buffer battery, the fuel cell and compressor would be sized sufficiently larger for the intended application, allowing the compressor to change speeds much faster. This in turn would allow power outputs to change much quicker. If power outputs can change as quickly as the application dictates, then a buffer battery is not necessary. In one or more embodiments, because the system is mostly electronically controlled, software can be written to protect the fuel cell from instantaneous power pikes. If a large power output is suddenly requested of the fuel cell, the software can smooth out the demand curve to provide an easier load profile to follow.

Abstract: Described is an electric vehicle conversion system and method comprising one or more battery packs disposed within one or more battery pack enclosures, a frontal mounting subframe assembly and an electric motor mounting frame assembly. In one implementation, the vehicle conversion system incorporates six battery pack enclosures. The described components and assemblies are designed to simplify building an electric car on the basis of an existing vehicle chassis. The frontal mounting subframe assembly is designed to be securely attached to the vehicle frame using at least four bolts and is designed to securely hold two battery pack enclosures disposed under the front hood of the vehicle. The electric motor mounting frame assembly is designed to mechanically mate with the existing engine mounting points of the original vehicle and is attached to said points with at least two bolts.