An electrical control and power supply system for at least one helicopter motor/generator, the system including a first DC/AC converter selectively delivering AC electrical power to the at least one motor/generator, depending on respective positions of contactors of a connection matrix actuated from an electronic control circuit, the first DC/AC converter powered with DC by a DC power supply device that includes either a circuit for rectifying an AC voltage delivered via a contactor by a starter/generator of an APU, or a voltage booster DC/DC converter powered from a battery via a contactor. The connection matrix further includes a contactor connecting the first DC/AC converter in parallel with the second DC/AC converter to make it possible, once at least one of the motors/generators has started, to inject additional power from the starter/generator of the APU.
Control and power supply system for helicopter turbine engines
2017-08-29
Patent
Elektronische Ressource
Englisch
IPC: | F02N STARTING OF COMBUSTION ENGINES , Anlassen von Brennkraftmaschinen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02J CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER , Schaltungsanordnungen oder Systeme für die Abgabe oder Verteilung elektrischer Leistung |
ENGINES - Helicopter engines power ahead
Online Contents | 2005
Multifuel operation with helicopter gas turbine engines
Engineering Index Backfile | 1961
|Air Bleed Objective for Helicopter Turbine Engines
SAE Technical Papers | 1997
AIR BLEED OBJECTIVE FOR HELICOPTER TURBINE ENGINES
SAE Technical Papers | 1983
AIR BLEED OBJECTIVE FOR HELICOPTER TURBINE ENGINES
SAE Technical Papers | 1969