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Standard

Document for Electric Power Management

2017-09-24
WIP
ARP5584A
This SAE Aerospace Recommended Practices (ARP) covers the definitions, functions and broad application guidelines of modern aerospace vehicle electric power management systems. As aerospace control systems have become more sophisticated and autonomous, the electric power subsystem no longer is just a generation and distribution bus control system. New electric power systems include integration of individual load logic control, protection, generation, distribution, and load management. This system can report to a higher level control system, typically a vehicle management system, or can be an autonomous system within itself reporting and responding to operator commands.
Standard

Lithium Battery Systems – Prognostics and Health Management

2015-12-10
WIP
AIR6897
This AIR is intended to provide basic guidance on the features that should be considered for implementation when contemplating the design and development of rechargeable lithium battery systems for utilization onboard aircraft. These guidelines will apply to “installed” equipment which would be part of the original or supplemental type certification or military airframe qualification.
Standard

Design and Development of Rechargeable Aerospace Lithium Battery Systems

2015-07-29
WIP
AIR6343
This AIR is intended to provide basic guidance on the methodologies that should be utilized when contemplating the design and development of rechargeable lithium battery systems for utilization onboard aircraft. These guidelines will apply to “installed” equipment which would be part of the original or supplemental type certification or military airframe qualification.
Standard

Solid State Power Controller, General Standard For

2015-04-15
WIP
AS4805A
This SAE Aerospace Standard (AS) covers the general requirements for the design, manufacture, and test of Solid State Power Controllers (SSPCs) of both dc and ac ratings for use in electrical power systems. SSPCs conforming to this standard are intended for use in controlling the making and breaking of power circuits for electrically operated equipment and devices, and for providing overload and short-circuit protection.
Standard

Lithium Battery Powered Portable Electronic Devices

2013-10-04
CURRENT
AIR5561
This SAE Aerospace Information Report (AIR) is intended to cover any type of portable electronic device, powered by a rechargeable lithium battery that has application in operating the aircraft. This includes devices such as laptop computers, electronic tablets, and electronic book-reading devices, used as Electronic Flight Bags (EFBs), and similar applications.
Standard

Minimum Performance Standards for Aerospace Electric Power Converters

2011-07-21
CURRENT
AS4361A
This SAE Aerospace Standard (AS) establishes the minimum performance standards for equipment used as secondary direct current (DC) electrical power sources in aerospace electric power systems. The purpose of this document is to define the guidelines and minimum performance test standards to be met by static electric power converters designed to operate from primary electric power systems. The tests specified herein provide a laboratory means to determine the performance and reliability characteristics of electric power converters under electrical and environmental conditions representative of these encountered in actual aerospace applications.
Standard

ARC Fault Interrupter, 270 VDC

2009-11-17
WIP
AS6087
Develop a standard for testing and evaluating direct current arc fault detection and interruption technologies.
Standard

Solid State Power Controller, General Standard For

2007-07-23
CURRENT
AS4805
This SAE Aerospace Standard (AS) covers the general requirements for the design, manufacture, and test of Solid State Power Controllers (SSPCs) of both dc and ac ratings for use in electrical power systems. SSPCs conforming to this standard are intended for use in controlling the making and breaking of power circuits for electrically operated equipment and devices, and for providing overload and short-circuit protection.
Standard

Document for Electric Power Management

2002-03-29
CURRENT
ARP5584
This SAE Aerospace Recommended Practices (ARP) covers the definitions, functions and broad application guidelines of modern aerospace vehicle electric power management systems. As aerospace control systems have become more sophisticated and autonomous, the electric power subsystem no longer is just a generation and distribution bus control system. New electric power systems include integration of individual load logic control, protection, generation, distribution, and load management. This system can report to a higher level control system, typically a vehicle management system, or can be an autonomous system within itself reporting and responding to operator commands.
Standard

Minimum Performance Standards for Airborne Static Electric Power Inverters

1985-09-01
HISTORICAL
AS8023
The purpose of this document is to define the minimum performance requirements to be met by static electric power inverters designed for use in civil aircraft. The tests specified herein provide a laboratory means to determine the performance characteristics of static electric power inverters under electrical and environmental conditions representative of those encountered in actual aeronautical operation.
Standard

Nickel Cadmium Vented Rechargeable Aircraft Batteries (Non-Sealed, Maintainable Type)

1981-02-15
CURRENT
AS8033
The Nickel Cadmium battery covered by this Aerospace Standard is the type which is generally, although not exclusively, used for engine starting purposes in turbine-powered aircraft and/or on aircraft with turbine type Auxiliary Power Units. This turbine starting function requires high power delivery rates from the battery for 15 to 30 seconds or more for each engine start. This same battery may also be used at lower power delivery rates, as the final redundant source of emergency electrical energy for the operation of essential flight equipment for required periods of 30 to 60 minutes. The battery generally consists of a group of plastic jarred cells contained within an enclosing battery case. They are electrically connected in series with each other and usually terminate in an electrical connector mounted in the case front wall. The battery case may be secured to the aircraft structure by any of a number of clamping techniques.
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