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ARC Fault Interrupter, 270 VDC

Develop a standard for testing and evaluating direct current arc fault detection and interruption technologies.

Solid State Power Controller, General Standard For

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.

Lithium Battery Powered Portable Electronic Devices

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.

Document for Electric Power Management

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.

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

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.