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This paper proposes a current limits distribution control strategy for a parallel hybrid electric vehicle (parallel HEV) which includes an advanced powertrain concept with two electrical driving axles. One of the difficulties of an HEV powertrain with two electrical driving axles is the ability to distribute the electrical current of one high voltage battery appropriately to the two independent electrical motors. Depending on the vehicle driving condition (i.e., car maneuver) or the maximization of the entire efficiency chain of the system, a suitable control strategy is necessary. We propose an input-output feedback linearization strategy to cope with the nonlinear system subject to input constraints. This approach needs an external, state dependent saturation element, which translates the state dependent control input saturation to the new feedback linearizing input and therefore preserves the properties of the differential geometric framework.

Abstract Carbon fiber reinforced plastic (CFRP) has been used in automobiles as well as airplanes. Because of its light weight and high strength, CFRP is a good choice for making vehicle bodies lighter, which would improve fuel economy. Conventional metal bodies provide a convenient body return for electric wiring and offer good shielding against electromagnetic fields. Although CFRP is a conductor, its conductivity is much lower than that of metals. Therefore, CFRP bodies are usually not useful for electric wiring. In thunderstorms, an automotive body is considered to be a Faraday cage that protects the vehicle’s occupants from the potential harms of lightning. Before CFRP becomes widely applied to automotive bodies, its electric and electromagnetic properties need to be investigated in order to determine whether it also works as a Faraday cage against lightning. In this article, CFRP and metal body vehicles were tested under artificial lightning.

Abstract A key problem of the construction of fully electric aircraft is the limited energy density of battery packs. It is generally accepted that this can only be overcome via new, denser battery chemistry together with a further increase in the efficiency of power utilization. One appealing approach for achieving the latter is using laser-assisted filler-based joining technologies, which offers unprecedented flexibility for achieving battery cell connections with the least possible electrical loss. This contribution presents our results on the effect of various experimental and process parameters on the electrical and mechanical properties of the laser-formed bond.

This activity is focused on more electric and all electric type power systems for air vehicles. The scope of which includes source, distribution and user contributions to electrical power quality, failure modes, coordination, system reliabilty and robustness, impacts of being flight critical and the gaps which exist in present standards and guidance documents.

This SAE Aerospace Information Report is intended to provide advanced methods for wire selecting and sizing in aerospace application as a continuation of AIR6540, Fundamentals in Wire Selection and Sizing for Aerospace Applications. Also, it will provide valuable information for the electrical design engineer to verify the proper wire selection and validate a set of system design requirements which includes meeting environmental and installation constraints.

EPS stability is an essential property that defines EPS ability to provide secure operation under required range of operation scenario. Power system stability is defined as “the ability of an electric power system, for a given initial operating condition, to regain a state of operating equilibrium after being subjected to a physical disturbance, with most system variables bounded so that practically the entire system remains intact”. This is applicable for AC and DC systems and has to address steady state conditions, transient conditions as well as high power loads connection / disconnection on the network.

The need for developing this standard is driven by the quickly evolving field of electrified propulsion for aircraft. Industry is moving forward in development of a broad range of high voltage primary power systems. There is an immediate need to standardize power quality requirements for design, analysis, verification, and testing for these types of systems.

Technical requirements especially related to the design and construction and the minimum performance requirements (including qualification test conditions) for PM motors and power converters (operated as VFDs) used as the prime mover for more-electric, hybrid-electric, and fully-electric aircraft propulsion systems.

This AIR intends to better document and tabulate electrical load dynamics that influence power source capacity, power quality and stabiltiy.

To determine the end-of-life criteria of electrical insulation materials and components and predict insulation life in high voltage aviation applications

To provide test guidelines, recommendations and referenced standards for insulation materials in a high energy system especially at high voltages (AC, DC and PWM) and at high altitudes, in the purpose of defining/measuring the effects of insulation ageing.

This specification covers resin-bonded glass fibers in the form of felted pads, flat or in rolls.

This specification covers resin-bonded glass fibers in the form of felted pads, flat or in rolls.

This specification covers an electrically-conductive adhesive supplied as two components, a silver-filled, epoxy-base adhesive and a separate curing agent which may be paste or liquid.

This specification covers an electrically-conductive adhesive supplied as two components, a silver-filled, epoxy-base adhesive and a separate curing agent which may be paste or liquid.