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RU2005136774A - METHOD FOR MANAGING POWER PLANE OF AIRCRAFT - Google Patents

METHOD FOR MANAGING POWER PLANE OF AIRCRAFT Download PDF

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Publication number
RU2005136774A
RU2005136774A RU2005136774/06A RU2005136774A RU2005136774A RU 2005136774 A RU2005136774 A RU 2005136774A RU 2005136774/06 A RU2005136774/06 A RU 2005136774/06A RU 2005136774 A RU2005136774 A RU 2005136774A RU 2005136774 A RU2005136774 A RU 2005136774A
Authority
RU
Russia
Prior art keywords
aircraft
engine
power plant
thrust
mode
Prior art date
Application number
RU2005136774/06A
Other languages
Russian (ru)
Other versions
RU2306446C1 (en
Inventor
Александр Александрович Иноземцев (RU)
Александр Александрович Иноземцев
Александр Николаевич Семенов (RU)
Александр Николаевич Семенов
Юрий Семенович Савенков (RU)
Юрий Семенович Савенков
Алексей Николаевич Саженков (RU)
Алексей Николаевич Саженков
Юрий Абрамович Трубников (RU)
Юрий Абрамович Трубников
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2005136774/06A priority Critical patent/RU2306446C1/en
Publication of RU2005136774A publication Critical patent/RU2005136774A/en
Application granted granted Critical
Publication of RU2306446C1 publication Critical patent/RU2306446C1/en

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  • Combined Controls Of Internal Combustion Engines (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)

Claims (3)

1. Способ управления силовой установкой самолета, включающий измерение параметров тяги двух двигателей силовой установки, сравнение их значений с заданной величиной, необходимой для включения режима повышенной тяги, измерение положений рычагов управления двигателей, сравнение их с заданными значениями, соответствующими взлетному режиму самолета, при неисправности или отказе одного двигателя включение режима повышенной тяги другого двигателя, отличающийся тем, что дополнительно измеряют воздушную скорость самолета Vc, сравнивают Vc с заданной величиной Vc зад, формируют сигнал IП "предкрылки не убраны" и IТ "стояночный тормоз выключен", а режим повышенной тяги исправного двигателя включают при Vc>Vc зад, и наличии сигналов IП и IТ.1. The method of controlling the aircraft power plant, including measuring the thrust parameters of two engines of the power plant, comparing their values with a predetermined value necessary to activate the high thrust mode, measuring the positions of the engine control levers, comparing them with the set values corresponding to the takeoff mode of the aircraft, in case of malfunction or failure of one engine, the inclusion of increased thrust of another engine, characterized in that it additionally measure the airspeed of the aircraft V c , compare V c with set value V c back , form a signal I P "slats are not removed" and I T "parking brake is applied", and the increased thrust mode of a working engine is turned on at V c > V c back , and there are signals IP and I T. 2. Способ управления силовой установкой самолета по п.1, где в качестве заданной воздушной скорости самолета Vc зад используют скорость принятия решения о взлете Vвзл.2. The method of controlling the aircraft power plant according to claim 1, where as the given airspeed of the aircraft V c ass , the decision-making speed of take-off V take-off is used . 3. Способ управления силовой установкой самолета по п.1, где в качестве параметра тяги двигателя используют суммарный сигнал частоты вращения вентилятора nв и ее первой производной dnв/dt в виде nв+С·dnв/dt, где С - весовой коэффициент, зависящий от динамических свойств ротора вентилятора двигателя.3. The control method of the aircraft power plant according to claim 1, where as the engine thrust parameter use the total signal of the fan speed n in and its first derivative dn in / dt in the form n in + C · dn in / dt, where C is the weight a coefficient depending on the dynamic properties of the rotor of the engine fan.
RU2005136774/06A 2005-11-25 2005-11-25 Method of control of aircraft power plant RU2306446C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2005136774/06A RU2306446C1 (en) 2005-11-25 2005-11-25 Method of control of aircraft power plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2005136774/06A RU2306446C1 (en) 2005-11-25 2005-11-25 Method of control of aircraft power plant

Publications (2)

Publication Number Publication Date
RU2005136774A true RU2005136774A (en) 2007-05-27
RU2306446C1 RU2306446C1 (en) 2007-09-20

Family

ID=38310490

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005136774/06A RU2306446C1 (en) 2005-11-25 2005-11-25 Method of control of aircraft power plant

Country Status (1)

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RU (1) RU2306446C1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110621858A (en) * 2017-04-03 2019-12-27 赛峰直升机发动机公司 Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2497001C1 (en) * 2012-05-10 2013-10-27 Открытое акционерное общество "СТАР" Method of controlling fuel feed to gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110621858A (en) * 2017-04-03 2019-12-27 赛峰直升机发动机公司 Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines
CN110621858B (en) * 2017-04-03 2022-02-08 赛峰直升机发动机公司 Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Also Published As

Publication number Publication date
RU2306446C1 (en) 2007-09-20

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