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Space Power Standard

AE-7C Systems
  • Aerospace Standard
  • AS5698A
  • Current
Published 2018-09-13 by SAE International in United States
This standard defines the requirements and characteristics of electrical power for spacecraft. This standard also defines analysis, verification, and testing methodologies to be used to ensure that the loads operate when connected to the specified power quality and performance as defined by this standard.
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Radioisotope Power Systems

AE-7C Systems
  • Aerospace Standard
  • AIR1213A
  • Current
Published 2017-11-30 by SAE International in United States
No Abstract Available.
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Document for 270 Voltage Direct Current (270 V DC) System

AE-7C Systems
  • Aerospace Standard
  • ARP4729A
  • Current
Published 2017-11-30 by SAE International in United States
This SAE Aerospace Recommended Practice (ARP) provides technical design and application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. This document also provides references and definitions to permit comparisons of various electrical systems and components.
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Electrical Power, 270 V DC, Aircraft, Characteristics and Utilization of

AE-7C Systems
  • Aerospace Standard
  • AS1831A
  • Current
Published 2017-10-26 by SAE International in United States
This SAE Aerospace Standard (AS) establishes the characteristics and utilization of 270 V DC electric power at the utilization equipment interface and the constraints of the utilization equipment based on practical experience. These characteristics shall be applicable for both airborne and ground support power systems. This document also defines the related distribution and installation considerations. Utilization equipment designed for a specific application may not deviate from these requirements without the approval of the procuring activity.
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Managing Higher Voltages in Aerospace Electrical Systems

AE-7C Systems
  • Aerospace Standard
  • AIR6127
  • Current
Published 2017-04-03 by SAE International in United States
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. It is noted that electrical systems for electrical propulsion may consider operating voltages beyond 1500 VAC/DC.
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Ways of Dealing with Power Regeneration onto an Aircraft Electrical Power System Bus

AE-7C Systems
  • Aerospace Standard
  • AIR6139
  • Current
Published 2014-01-14 by SAE International in United States
This SAE Aerospace Information Report (AIR) considers the issue of power regeneration into the EPS of an aircraft. A series of options for dealing with this regenerative power are considered and arranged in categories. Advantages and disadvantages of each solution, including the existing solution, are included. Validated simulation results from representative Electrical Power systems are presented in order to demonstrate how some of the solutions may operate in practice and how power quality can be maintained during regeneration. The impact on changes to the electrical generation system are also highlighted in this AIR, as these changes may have an impact on the solution deployed and the wider impact on the design of engines and auxiliaries. This AIR reviews concepts and excludes detailed discussions on power system design. These concepts relate to the More Electric Aircraft, cover both AC and DC systems and can be applied to both normal operating conditions or as fault mitigation.
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Electric Power, Aircraft, Characteristics and Utilization of

AE-7C Systems
  • Aerospace Standard
  • AS1212A
  • Current
Published 2012-12-05 by SAE International in United States
The standard delineates the characteristics of electric power supplied to airborne equipment at the equipment terminals and the requirements for the utilization of such electric power by the airborne equipment.
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Space Power Standard

AE-7C Systems
  • Aerospace Standard
  • AS5698
  • Historical
Published 2012-04-11 by SAE International in United States
This standard defines the requirements and characteristics of electrical power for spacecraft. This standard also defines analysis, verification, and testing methodologies to be used to ensure that the loads operate when connected to the specified power quality and performance as defined by this standard.
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Cryogenically Fueled Dynamic Power Systems

AE-7C Systems
  • Aerospace Standard
  • AIR999A
  • Current
Published 2011-08-03 by SAE International in United States
In this report, "Cryogenically Fueled Dynamic Power Systems" include all open cycle, chemically fueled, dynamic engine power systems which utilize cryogenic fuels and oxidizers. For nearly all practical present day systems, this category is limited to cryogenic hydrogen or hydrogen-oxygen fueled cycles with potential in future, more advanced systems for replacement of oxygen by fluorine. Excluded from the category are static cryogenic systems (e.g., fuel cells) and chemical dynamic power systems which utilize earth storable propellants.
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DOCUMENT FOR 270 VOLTAGE DIRECT CURRENT (270 V DC) SYSTEM

AE-7C Systems
  • Aerospace Standard
  • ARP4729
  • Historical
Published 2010-07-06 by SAE International in United States
This SAE Aerospace Recommended Practice (ARP) provides technical design and application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. This document also provides references and definitions to permit comparisons of various electrical systems and components.
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