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The closed-cycle hydrogen-fueled argon power cycle is a zero emissions concept that combines a carbon-free fuel with argon as a diluent replacement for nitrogen. The lack of nitrogen in the argon power cycle results in zero NOx emissions on an internal combustion engine platform. There is also massive efficiency improvement because argon is monatomic and has a very high ratio of specific heats. However, this will also result in combustion temperatures and pressures exceeding those normally achieved on an air-standard engine platform. The literature shows conflict between modeling, which promises incredibly high efficiency gains, and experiment, which show more modest efficiency gains. This work combined thermodynamic modeling, literature analysis, and experiments to understand this discrepancy and ultimately understand what level of efficiency gain can be expected for the argon power cycle. It was found that while low compression ratio engines stand to see the largest relative
Gainey, BrianAhrling, ChristofferTunestal, PerTuner, Martin
This SAE Standard applies to lead-acid 12 V heavy-duty storage batteries as described in SAE J537 and SAE J930 for uses in starting, lighting, and ignition (SLI) applications on motor vehicles and/or off-road machines. These applications have some of the following characteristics: High levels of power are required to start the vehicle’s internal combustion engine. The need to supply this power limits the maximum depth of discharge to a fraction of the total capacity of the battery. The battery must be maintained at a charge level sufficient to perform this primary function by the vehicle’s voltage-regulated charging system. The vehicle’s engine powers a voltage-regulated charging system that limits the charging voltage when spinning at sufficient speed and when total loads do not exceed its output limits. The battery is subject to deeper discharging than a typical automotive application as a result of the following conditions: High daily hours of use High numbers of starts per day
Starter Battery Standards Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Recommended Practice describes the recommended methods for testing flexible harness coverings for use on ground vehicle electrical distribution systems. It shall apply to all tapes, extruded tube, and textile tube.
Harness Covering Standards Committee
This SAE Aerospace Standard (AS) covers any protective system that serves the stated purpose.
A-10 Aircraft Oxygen Equipment Committee
This practice provides a method for evaluating microhardness and microstructure very close (0.002 inch (0.051 mm) or less) to the surface of a disk specimen. Specific accept/reject criteria for partial decarburization (3.7.1), inadvertent carburization/nitriding (3.7.3), total decarburization/intergranular oxidation (3.8), and other characteristics evaluated are to be found in the applicable specification where this ARP is referenced.
AMS E Carbon and Low Alloy Steels Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Standard establishes the requirements for a V-retainer coupling, flanges, and seal suitable for joining high-pressure and high-temperature ducting in aircraft bleed air systems. The rigid coupling joint assembly, hereafter referred to as “the joint,” shall operate within the temperature range of -65 to +1200 °F.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
During idling tests of a newly developed sport utility vehicle (SUV) under tropical high-temperature conditions, the condenser surface temperature exceeded the allowable range, degrading the air-conditioning system’s cooling performance. In this study, a three-dimensional computational fluid dynamics (CFD) model of the engine compartment flow field was established using STAR-CCM+. The results reveal that under idling conditions, the kinetic energy of hot air passing through the cooling module was insufficient to overcome the pressure difference between the front and rear sections, thus inducing hot air recirculation (HAR) and increasing the overall compartment temperature. To address the unfavorable flow field characteristics, four structural improvements were proposed and simulated for both flow and temperature fields. Through comparative analysis, the optimal scheme was determined: installing a flow guide baffle above the engine. Simulation results show that the airflow velocity
Shi, HuojieRao, R.H.Chen, J.Zheng, Z.L.
This article presents a novel finite element modeling approach to predict the mechanical response of jellyrolls in large-scale explicit crash simulations up to the experimental occurrence of internal short-circuit. The proposed simplified layered model embeds membrane elements within a solid element mesh to improve the prediction in load cases dominated by the buckling and sliding of the jellyroll’s layered structure. The model was validated against experimental results from in-plane, out-of-plane, and bending tests on jellyroll samples extracted from prismatic lithium-ion cells. The experimental results confirmed the jellyroll’s high compressibility under out-of-plane loads and its behavior as a collection of unconnected layers under in-plane and bending loading. Compared to the widely used crushable foam model, the simplified layered model offered additional flexibility, especially for in-plane and bending load cases. Additionally, it meets critical time increment requirements for
Cioni, DanieleMorin, DavidStrating, ArjanKizio, StephanCostas, Miguel
This specification, in conjunction with the general requirements for steel heat treatment covered in AMS2759, establishes the requirements and procedures for three classes of gas, vacuum, liquid, and low-pressure carburizing (LPC) and related heat treatment of parts fabricated from carburizing-grade steels. Parts made from steels other than those specified in the detail specifications may be heat treated in accordance with the applicable requirements using processing temperatures, times, and other parameters recommended by the material producer. This specification does not cover pack carburizing.
AMS B Finishes Processes and Fluids Committee
This SAE Aerospace Recommended Practice (ARP) provides information and guidance for the control of hazardous laser exposure in the navigable airspace. This ARP does not address techniques that pilots can apply to mitigate laser illuminations during a critical phase of flight. Such mitigation strategies are described in ARP6378.
G-10T Laser Safety Hazards Committee
This specification covers a copper alloy (phosphor bronze) in the form of sheet, strip, and plate (see 8.6).
AMS D Nonferrous Alloys Committee
This specification covers an aluminum alloy in the form of plate 0.500 to 4.500 inches (12.7 to 114.3 mm), inclusive, in nominal thickness (see 8.5).
AMS D Nonferrous Alloys Committee
This document applies to laser proponents involved with the use of laser systems outdoors. It may be used in conjunction with AS4970, ARP5535, ARP5572, and the ANSI Z136 series of laser safety standards.
G-10T Laser Safety Hazards Committee
Highly integrated electrical and electronic systems that perform functions within an aircraft may have potential failure conditions during and after exposure to the High-Intensity Radiated Fields (HIRF) or lightning environments. It is therefore necessary to conduct an HIRF and Lightning Safety Assessment (HLSA) that can identify potential failure conditions resulting from exposure to the aircraft HIRF and lightning environments. The failure conditions, failure conditions classifications, and independence principles identified by Aircraft Functional Hazard Assessment (AFHA), Preliminary Aircraft Safety Assessment (PASA), System Functional Hazard Assessment (SFHA), and Preliminary System Safety Assessment (PSSA), and lessons learned from previous experience, are used to identify proposed requirements during the development process. Ultimately, these requirements will result in a design capable of demonstrating that exposure to the HIRF and lightning environments will not result in
AE-4 Electromagnetic Compatibility (EMC) Committee
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This document provides guidance concerning the maintenance and serviceability of oxygen cylinders beginning with the quality of oxygen that is required, supplemental oxygen information, handling and cleaning procedures, transfilling, and marking of serviced oxygen assemblies. This document attempts to outline in a logical sequence oxygen quality, serviceability, and maintenance of oxygen cylinders. Content of this document can also be used for refilling oxygen cylinders while installed on aircraft, directly or through an intermediate charging port.
A-10 Aircraft Oxygen Equipment Committee