Alternator:
The alternator system consists of an alternator and an alternator-regulator device.
The alternator provides the following main properties:
ï‚· Air-cooled synchronous three-phase alternator with a claw-pole rotor
ï‚· Built-in semiconductor rectifier
ï‚· Stator winding circuit: delta connection
ï‚· External alternator regulator (mounted on the aircraft)
ï‚· Belt-driven by the engine
There are three external terminal points on the alternator:
ï‚· Power output (connected with battery)
ï‚· Excitation current input
ï‚· Ground (housing)
The output voltage of the alternator has to be constant, independent from engine speed and actual
load current. This requires a regulation of the output voltage by a variation of the excitation current
(implemented in the alternator-regulator device).
To avoid damage of the alternator the regulator must be deactivated when the engine
is not running.
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