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Specification of a high strength aluminum alloy for production of aerospace components using AM processes

Eco Approach and Departure (Eco-AnD) is a Connected Automated Vehicle (CAV) technology aiming to reduce energy consumption for crossing a signalized intersection or set of intersections in a corridor that features vehicle-to-infrastructure (V2I) communication capability. This research focuses on developing a Dynamic Programming (DP) based algorithm for a PHEV operating in Charge Depleting mode. The algorithm used the Reduced Order Energy Model (ROM) to capture the vehicle powertrain characteristics and road grade to capture the road dynamics. The simulation results are presented for a real-world intersection and 20-25% energy benefits are shown by comparing against a simulated human driver speed profile. The vehicle-level validation of the developed algorithm is carried out by performing closed-course track testing of the optimized speed solutions on a real CAV vehicle.

The AutoDrive Challenge competition sponsored by General Motors and SAE gives undergraduate and graduate students an opportunity to get hands-on experience with autonomous vehicle technology and development as they work towards their degree. Michigan Technological University has participated in the AutoDrive Challenge since its inception in 2017 with students participating through MTU’s Robotic System Enterprise. The MathWorks Simulation Challenge has been a component of the competition since its second year, tasking students with the development of perception, control and testing algorithms using MathWorks software products. This paper presents the pedagogical approach graduate student mentors used to enable students to build their understanding of autonomous vehicle concepts using familiar tools. This approach gives undergraduate students a productive experience with these systems that they may not have encountered in coursework within their academic program.

This research investigates the energy savings achieved through eco-driving controls in connected and automated vehicles (CAVs), with a specific focus on the influence of powertrain characteristics. Eco-driving strategies have emerged as a promising approach to enhance efficiency and reduce environmental impact in CAVs. However, uncertainty remains about how the optimal strategy developed for a specific CAV applies to CAVs with different powertrain technologies, particularly concerning energy aspects. To address this gap, on-track demonstrations were conducted using a Chrysler Pacifica CAV equipped with an internal combustion engine (ICE), advanced sensors, and vehicle-to-infrastructure (V2I) communication systems, compared with another CAV, a previously studied Chevrolet Bolt electric vehicle (EV) equipped with an electric motor and battery.

The turbine-engine-inlet flow distortion descriptors summarized in this document apply to the effects of inlet total-pressure, planar-wave, and total-temperature distortions. Guidelines on stability margin, destabilizing influences, types and purposes of inlet data, AIP definition, and data acquisition and handling are summarized from AIR5866, AIR5867, ARP1420, and AIR1419. The degree to which these recommendations are applied to a specific program should be consistent with the complexity of the inlet/engine integration. Total-pressure distortion is often the predominant destabilizing element that is encountered and is often the only type of distortion to be considered, i.e, not all types of distortion need to be considered for all vehicles.

This specification covers a corrosion and heat-resistant martensitic precipitation hardening stainless steel alloy in the form of pre-alloyed powder.

This specification covers a corrosion-resistant steel alloy in the form of parts produced by laser-powder bed fusion (L-PBF) that are subjected to post-deposition hot isostatic press (HIP), solution and precipitation heat treated (H1025) condition. The application is for parts typically requiring corrosion resistance and high strength up to 600 °F (316 °C) with good ductility and strength, but usage is not limited to such applications.

This standard has notes/guidance narratives interspersed throughout. These notes/guidance narratives are identified by a header and by text in italics.This standard defines a series of requirements that results in a specific AM machine qualified to produce material (see GN1) in compliance to an aerospace materials specification. The machine control and/or configuration types are discussed in the next sections.

Material specifications for parts manufactured using HPA1(12Si-4Cu-0.4Mg-0.5Fe-1.0Ti) powder

Aluminum alloy powder developed for the LPBF process for aerospace components

• AIRBAG COMPONENT MINIMUM PERFORMANCE REQUIREMENTS • AIRBAG INSTALLATION PERFORMANCE REQUIREMENT Current revision will only contain Part 25 and lapbelt installed airbags. Future revisions will expand to include Structural airbags, 3-point restraint airbag, pre-tensioner etc.

Scope is unavailable.

This SAE Aerospace Recommended Practice (ARP) provides guidance for the design of flanges on temperature sensors intended for use in gas turbine engines. Three figures detail the configuration of standard size flange mounts with bolt holes, slotted flanges, and miniaturized flanges for small probes.

This SAE Aerospace Recommended Practice (ARP) defines the nomenclature of temperature measuring devices. General temperature measurement related terms are defined first, followed by nomenclature specifice to temperature measuring devices, particularly thermocouples.

This SAE Aerospace Information Report (AIR) provides information and guidance for the selection and use of technologies and methods for lubrication system monitoring of gas turbine aircraft engines. This AIR describes technologies and methods covering oil system performance monitoring, oil debris monitoring, and oil condition monitoring. Both on-aircraft and off-aircraft applications are presented. A higher-level view of lubrication system monitoring as part of an overall engine monitoring system (EMS), is discussed in ARP1587. The scope of this document is limited to those lubrication system monitoring, inspection and analysis methods and devices that can be considered appropriate for health monitoring and routine maintenance. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard.

This specification covers preforms fabricated up through 5.5 inches (140 mm) inclusive in deposition width thickness (see 8.2.5) using a Plasma Arc Directed Energy Deposition (PA-DED) additive manufacturing process on a Ti-6Al-4V substrate that are subjected to post-deposition stress relief heat treatment. This is a wire fed additive manufacturing process. If required by the CEO, preforms may require subsequent machining to meet requirements for their intended final part application.

This SAE Aerospace Information Report (AIR) provides information regarding guidance when utilizing an SHM system for “airworthiness credits”. This document is applicable to civil fixed-wing aerospace airframe structural applications where stakeholders are seeking guidance on the approvals of structural health monitoring (SHM) technologies for aircraft health management applications. While this initial guidance is from the United States’ Federal Aviation Administration (FAA), Technical Innovation Policy Branch, other regulatory agencies may elect to add requirements as needed. Future revisions to this document could include the guidance from other regulatory agencies. This document does not teach how to design an SHM function, how to do a safety or risk analysis, prescribe hardware or software assurance levels, or answer the question “how much mitigation and evidence are enough.”

Specification template for titanium alloy powders.

This SAE Aerospace Recommended Practice (ARP) defines means to assess the effect of changes to seat back mounted IFE monitors on blunt trauma to the head and post-impact sharp edges. The assessment methods described may be used for evaluation of changes to seat back monitor delethalization (blunt trauma and post-test sharp edges) and head injury criterion (HIC) attributes (refer to ARP6448 Appendix A Items 3 and 6, respectively). Application is focused on type A-T (transport airplane) certified seat installations.

This document provides background information, rationale, and data (both physical testing and computer simulations) used in defining the component test methods and similarity criteria described in SAE Aerospace Recommended Practice (ARP) 6330. ARP6330 defines multiple test methods uses to assess the effect of seat back mounted IFE monitor changes on blunt trauma to the head and post-impact sharp edge generation. The data generated is based on seat and IFE components installed on type A-T (transport airplane) certified aircraft. While not within the scope of ARP6330, generated test data for the possible future development of surrogate target evaluation methods is also included.