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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 SAE Aerospace Information Report addresses the key factors contributing to high-voltage aging to be considered in EWIS design, manufacture, substantiation (qualification) testing, lot acceptance testing, and installation. Special considerations and information are provided to focus on Advanced Air Mobility applications (including Urban Air Mobility, eVTOL/eSTOL/eCTOL, and hybrid-electric commercial aircraft pursuing certification under 14 CFR 21.17(b), Part 23, Part 25, and/or Part 33), utilizing voltage within the VL-3/VL-4 ranges defined by SAE AIR7502. However, much of the information herein may be relevant to higher voltage levels and other applications.

This SAE Aerospace Recommended Practice (ARP) covers definitions, functions and broad application guidelines of electric load analysis and power source capacity planning and utilization in airborne platforms operated at high voltage DC (HVDC) and high voltage AC (HVAC) systems. These guidelines shall be applicable for both hybrid electric and all-electric propulsion schemes and dedicated ground support equipment. This document also defines the related distribution, integration, protection, and operational considerations, some of which may be outside of conventional power distribution and operations. Both propulsive and non-propulsive sources, systems, and loads and associated control systems comprise the new high voltage electric powerplant with individual load and source logic controls, protection, and power sources and load management that can report and receive commands from an autonomous vehicle management system or from an operator.

The scope of this project is to describe the applicability of Insulation monitoring devices (IMDs) for high voltage (HV) ungrounded systems. the basic advantages of using the IT system should be shown, and the requirements for the system, protection coordination, installation, and safety should be defined.

An SAE ARP (Aerospace Recommended Practice) document for the application of aerospace HV design standard for surface creepage (quantified for VDC, VAC, and frequency effects) including altitude and testing approach. Considering HV insulation system surface spacing with altitude affect testing approach and Test Article design to develop guidelines for material and spacing for voltage and altitude. Develop a testing procedure and dielectric test article for surface creepage with adjustable spacing. Initial testing effort using AC Vrms at a variety of altitudes, then expanding testing standard to DC, transients, temperatures, etc.

The scope of this report is first to establish applicable definitions and terms prior to considering the application domain and use cases in HVDC applications. Then it will describe the specificities of pyrotechnic actuator for use within a power switching device with order of magnitude in term of performances and main characteristics to consider for aerospace application.

This Aerospace Recommend Practice (ARP) document provides ways of designing high voltages systems in aerospace vehicles. It is intended to provide recommended design and testing considerations associated with level 4 and 5 voltages, per AIR 7502, in aerospace electrical systems. Key areas of concern when using high voltage in aerospace applications are power conversion equipment and the components within them. The interaction between components and subsystems will be discussed. This document will also provide a basis for identifying high voltage design risks, defines areas of concern as a function of environment, and potential risk mitigation methods.

This document discusses isolation failures in high voltage battery systems in testing and service, conditions that may lead to the development of those failures, and successful methods of mitigation.

This document aims to capture technology particularities and intrinsic failure modes specific to permanent magnet (PM) machines, in relation to traditional wound field machines, both from the design performances stand points. It will identify specific failure modes and propose ways of mitigations to consider for their safe design and usages.

The scope of this report is first to establish applicable definitions and general specification and terms prior to considering the application domain and use cases in HVDC applications. Then it will describe the methods of protection and system level coordination to and define different coordinated protection schemes to consider for aerospace application.

The scope of this SAE Aerospace Information Report (AIR) is first to establish applicable definitions and terms prior to considering the application domain and use cases in HVDC applications. Then it will identify commanded switching technologies to be considered for aerospace applications and provide rationale for their selection.

This SAE Aerospace Information Report (AIR) considers the issue of proper design guidance for high voltage electrical systems used in aerospace applications. This document is focused on electrical discharge mechanisms including partial discharge and does not address personnel safety. Key areas of concern when using high voltage in aerospace applications are power conversion devices, electrical machines, connectors and cabling/wiring. The interaction between components and subsystems will be discussed. The AIR is intended for application to high voltage systems used in aerospace vehicles operating to a maximum altitude of 30000 m (approximately 100000 feet), and maximum operating voltages of below 1500 VRMS (AC)/1500 V peak (DC). These upper voltage limits have been incorporated because this report focuses on extending the operating voltage of non-propulsive electrical systems beyond that of existing aerospace systems.