IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0575286
(2009-10-07)
|
등록번호 |
US-8249792
(2012-08-21)
|
우선권정보 |
FR-08 05576 (2008-10-09) |
발명자
/ 주소 |
- Blanvillain, Emmanuel
- Constans, Florian
- Chabe, David
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
Disclosed is a method and device for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine. A control unit is triggered
Disclosed is a method and device for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine. A control unit is triggered to activate a protection function, as a function of the number and position of failed engines. The control unit controls at least one non-failed engine, and the protection function is activated when activation conditions are met. The activation conditions indicate that the aircraft is either in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power.
대표청구항
▼
1. A method for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine, the method comprising the steps of: detecting eng
1. A method for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine, the method comprising the steps of: detecting engine failure;measuring a plurality of parameters of said aircraft;triggering a control unit to activate a protection function, as a function of the number and position of failed engines, and control at least one non-failed engine of said aircraft, wherein the protection function is activated when activation conditions are met, with the activation conditions indicating that the aircraft is in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power,wherein said triggering is carried out by a triggering unit, in which the triggering unit is configured to: A)—calculate a speed threshold of said aircraft from at least one of the measured parameters; andB)—determine from said calculated speed threshold, a total power to be applied to said engines of the aircraft in order to maintain the calculated speed threshold; andwherein said control unit is configured to: C)—determine, upon triggering by the triggering unit, a modification of power to each controlled non-failed engine such that a sum of the determined modified individual power to each of said controlled engines and of individual current power to each non-controlled engine is equal to the determined total power. 2. The method as claimed in claim 1, wherein the protection function is deactivated when at least one of the following conditions is met:said activation conditions are no longer met;all engines mounted on one and the same wing of said aircraft have simultaneously failed. 3. The method as claimed in claim 1, wherein:asymmetry in the individual current power of said controlled engines is detected; andupon detection of the asymmetry, the individual current power of said controlled engines is modified during step C) to reduce said power asymmetry. 4. The method as claimed in claim 1, wherein said activation conditions indicate the low-energy situation is met and said activation conditions comprise a first condition, and wherein:in step A), a minimum speed threshold is calculated;in step B), a minimum total power to maintain speed of said aircraft at least equal to said minimum speed threshold is determined;said first condition is met when the total current power of said aircraft is less than said determined minimum total power; andin step C), the power of said controlled engines is increased to avoid the low-energy situation. 5. The method as claimed in claim 1, wherein said activation conditions indicate the high-energy situation is met and said activation conditions comprise a first condition, wherein:in step A), a maximum speed threshold is calculated;in step B), a maximum total power to maintain speed of said aircraft of at most equal to said maximum speed threshold is determined;said first condition is met when the total current power of said aircraft is greater than said determined maximum total power; andin step C), the power of said controlled engines is decreased to avoid the high-energy situation. 6. The method as claimed in claim 4, wherein said activation conditions comprise a second condition to be met with said first condition, wherein said second condition is met according to the following:the aircraft altitude is greater than a predetermined altitude value, at the time of landing; anda plurality of particular systems of said aircraft are validated. 7. The method as claimed in claim 4, wherein:said protection function is deactivated through application of a deactivation unit; andupon deactivation, said modified individual power of said controlled engines is decreased to reach predetermined individual power values. 8. The method as claimed in claim 5, wherein:said protection function is deactivated through application of a deactivation unit; andupon deactivation, said modified individual power of said controlled engines is increased to reach predetermined individual power values. 9. An energy protection device for protecting an aircraft comprising at least one wing-mounted engine on each wing against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed-engine, said device comprising: detection unit that detects engine failure;measurement unit that measures a plurality of parameters of said aircraft;control unit that, upon triggering, activates a protection function, as a function of the number and position of failed engines, and controls at least one non-failed engine of said aircraft; andtriggering unit that monitors at least one of said measured parameters and triggers said control unit when activation conditions are met, with the activation conditions indicating that the aircraft is in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power,wherein the triggering unit comprises: calculation unit that calculates a speed threshold from at least one of said measured parameters; andpower determination unit that determines, from said calculated speed threshold, a total power to be applied to said engines in order to maintain the calculated speed threshold, andwherein the control unit comprises:modification unit that determines modification of power to each controlled non-failed engine such that a sum of the determined modified individual power of each of said controlled engines and of individual current power of each of the non-controlled engines is equal to the determined total power. 10. An aircraft, which comprises an energy protection device for protecting the aircraft comprising at least one wing-mounted engine on each wing against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed-engine, said device comprising: a detection unit that detects engine failure;a measurement unit that measures a plurality of parameters of said aircraft;a control unit that, upon triggering, activates a protection function as a function of the number and position of failed engines, and controls at least one non-failed engine of said aircraft; anda triggering unit that monitors at least one of said measured parameters and triggers said control unit when activation conditions are met, with the activation conditions indicating that the aircraft is in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power,wherein the triggering unit comprises: a calculation unit that calculates a speed threshold from at least one of said measured parameters; anda power determination unit that determines, from said calculated speed threshold, a total power to be applied to said engines in order to maintain the calculated speed threshold; andwherein the control unit comprises: a modification unit that determines modification of power to each controlled non-failed engine such that a sum of the determined modified individual power of each of said controlled engines and of individual current power of each of the non-controlled engines is equal to the determined total power.
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