[특허]Method of controlling the centre of gravity of an aircraft

Airbus Operations Limited

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Method of controlling the centre of gravity of an aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-017/10
미국특허분류(USC)	244/135C;
출원번호	US-0131209 (2008-11-25)
등록번호	US-8814096 (2014-08-26)
국제출원번호	PCT/GB2008/051110 (2008-11-25)
§371/§102 date	20110525 (20110525)
국제공개번호	WO2010/061156 (2010-06-03)
발명자 / 주소	Spottiswoode, Michael Burckhart, Antoine Sjungargard, Petter
출원인 / 주소	Airbus Operations Limited
대리인 / 주소	Lowe Hauptman & Ham, LLP
인용정보	피인용 횟수 : 1 인용 특허 : 6

초록

A method of controlling the center of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft.

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1. A method of controlling the centre of gravity of an aircraft having a plurality of fuel tanks, the method comprising calculating, upon detection of the failure of one or more fuel quantity indicators (FQI) associated with respective fuel tanks, a decrease in gross weight of the aircraft based on an amount of fuel used during flight, and transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the calculated decrease in gross weight of the aircraft. 2. The method of claim 1, wherein the predetermined sequence is arranged to maintain the centre of gravity of the aircraft between predetermined fore and aft limits. 3. The method of claim 1, wherein the plurality of fuel tanks includes a trim tank and the sequence comprises alternating between a fuel transfer from one or more of the fuel tanks other than the trim tank for the time taken for the gross weight to decrease by a first amount and a fuel transfer from the trim tank for the time taken for the gross weight to decrease by a second amount, the second amount being less than the first amount. 4. The method of claim 3, wherein the sequence of fuel transfers continues until the trim tank is declared empty. 5. The method of claim 4, wherein the trim tank is declared empty when a fuel pressure signal from a fuel pump located within the trim tank is below a threshold value for longer than a given period of time. 6. The method of claim 1, wherein the gross weight of the aircraft is calculated as the sum of a predetermined value for the weight of the aircraft with zero fuel on board and a value for the current fuel on board. 7. The method of claim 6, wherein the value for the current fuel on board is calculated as a value for the initial amount of fuel on board (FOBinit) minus the amount of fuel used. 8. The method of claim 7, wherein the value for the initial amount of fuel on board (FOBinit) is determined at the time when all the aircraft engines have started as the sum of fuel in each fuel tank. 9. The method of claim 8, wherein the amount of fuel in each fuel tank is manually entered. 10. The method of claim 7, wherein each fuel tank has an associated fuel quantity indicator and the value for the initial amount of fuel on board (FOBinit) is determined at the time when all the aircraft engines have started as the sum of an assigned value of fuel for each fuel tank having a failed associated fuel quantity indicator plus the sum of fuel in each of the remaining fuel tanks. 11. The method of claim 10, wherein the assigned value is in the range of zero to the maximum capacity of the fuel tank. 12. The method of claim 11, wherein the assigned value is manually entered. 13. The method of claim 12, wherein the manually entered value is zero. 14. The method of claim 1, wherein the decrease in gross weight of the aircraft is deemed equal to the weight of fuel used. 15. A method of controlling the centre of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft, wherein the gross weight of the aircraft is calculated as the sum of a predetermined value for the weight of the aircraft with zero fuel on board and a value for the current fuel on board,wherein the value for the current fuel on board is calculated as a value for the initial amount of fuel on board (FOBinit) minus the amount of fuel used,wherein each fuel tank has an associated fuel quantity indicator and the value for the initial amount of fuel on board (FOBinit) is determined at the time when all the aircraft engines have started as the sum of an assigned value of fuel for each fuel tank having a failed associated fuel quantity indicator plus the sum of fuel in each of the remaining fuel tanks,wherein the assigned value is in the range of zero to the maximum capacity of the fuel tank, and, wherein the assigned value is automatically set equal to the amount of fuel in one of the remaining fuel tanks having a functioning fuel quantity indicator.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

Moser, Matthew A.; Finn, Michael R.; Thoreen, Adam. Control interface for leading and trailing edge devices. USP2017059656741.

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Method of controlling the centre of gravity of an aircraft

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Method of controlling the centre of gravity of an aircraft

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이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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