FIELD: engines and pumps.
SUBSTANCE: proposed method comprises measuring time interval between reservoir capacitor discharge current sequential pulses that follows to ignition plug. Time interval exceeding preset magnitude allows deciding on ignition system integrity. Note here that measured is the time interval between discharge current pulses caused solely by commutation of power accumulated at reservoir capacitor that exceeds check magnitude.
EFFECT: higher validity of control, condition-based operation.
2 dwg
Title | Year | Author | Number |
---|---|---|---|
METHOD OF CONTROLLING AIRCRAFT ENGINES CAPACITIVE IGNITION SYSTEM | 2015 |
|
RU2608888C1 |
AIRCRAFT ENGINES CAPACITIVE IGNITION SYSTEM CONTROL DEVICE | 2015 |
|
RU2614388C2 |
CONTROL OVER AIRCRAFT ENGINE CAPACITIVE IGNITION SYSTEM | 2014 |
|
RU2558751C1 |
METHOD OF CONTROLLING CAPACITOR IGNITION UNIT WITH INDUCTION COIL AS PART OF IGNITION SYSTEM | 2015 |
|
RU2628224C2 |
METHOD OF CONTROLLING AIRCRAFT ENGINES CAPACITIVE IGNITION SYSTEM | 2018 |
|
RU2678231C1 |
METHOD OF CONTROLLING AIRCRAFT ENGINES CAPACITIVE IGNITION SYSTEM | 2018 |
|
RU2680724C1 |
CONTROL METHOD OF CAPACITIVE IGNITION UNIT | 2020 |
|
RU2738210C1 |
METHOD FOR MONITORING SERVICEABILITY OF HIGH-VOLTAGE CAPACITIVE IGNITION SYSTEMS OF GAS TURBINE ENGINES | 2021 |
|
RU2767662C1 |
AIRCRAFT GAS TURBINE ENGINE CAPACITIVE IGNITION SYSTEM CONTROL DEVICE | 2021 |
|
RU2767663C1 |
METHOD OF IGNITING AIRCRAFT GAS TURBINE COMBUSTION CHAMBER | 2011 |
|
RU2463522C1 |
Authors
Dates
2012-10-10—Published
2011-02-04—Filed