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Standard

Document for 270 Voltage Direct Current (270 V DC) System

2017-11-30
CURRENT
ARP4729A
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.
Standard

Fundamentals in selecting Wire Sizes in Aerospace Applications

2017-05-22
WIP
AIR6540
The scope of this report is to capture the fundamental principles of selecting a wire size for an aerospace application using the method prescribed in SAE AS50881 standard. Also, provided in this report are additional calculations to ensure the wire selection will adequately perform in a particular design function including meeting environment constraints. Some of the calculations in this report have been simplified to demonstrate the process for validating the wire size selections for a particular design application. More precise calculations should be investigated and evaluated to ensure proper assessment of each individual calculation in this report.
Standard

Managing Higher Voltages in Aerospace Electrical Systems

2017-04-03
CURRENT
AIR6127
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.
Standard

Space Power Standard

2015-12-16
WIP
AS5698A
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.
Standard

Ways of Dealing with Power Regeneration onto an Aircraft Electrical Power System Bus

2014-01-14
CURRENT
AIR6139
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.
Standard

Space Power Standard

2012-04-11
CURRENT
AS5698
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.
Standard

Cryogenically Fueled Dynamic Power Systems

2011-08-03
CURRENT
AIR999A
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.
Standard

Considerations for future more electric aircraft electric power systems

2011-05-06
WIP
AIR6198
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.
Standard

Electrical Power, 270 V DC, Aircraft, Characteristics and Utilization of

1997-10-01
CURRENT
AS1831A
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.
Standard

DOCUMENT FOR 270 VOLTAGE DIRECT CURRENT (270 V DC) SYSTEM

1992-09-18
HISTORICAL
ARP4729
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.
Standard

ELECTRICAL POWER, HIGH VOLTAGE DIRECT CURRENT, AIRCRAFT, CHARACTERISTICS AND UTILIZATION OF

1987-06-01
HISTORICAL
AS1831
This standard establishes the characteristics and utilization of 270-VDC electric power at the utilization equipment interface and the constraints on the utilization equipment. These characteristics shall be applicable for both airborne and ground support power systems. This standard also defines the related distribution and installation considerations. Utilization equipment designed for a specific aircraft application may not deviate from these requirements without the approval of the procuring activity.
Standard

ELECTRIC POWER, AIRCRAFT, CHARACTERISTICS AND UTILIZATION OF

1971-12-01
HISTORICAL
AS1212
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.
Standard

CRYOGENICALLY FUELED DYNAMIC POWER SYSTEMS

1968-10-01
HISTORICAL
AIR999
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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