[특허]Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft

Airbus Operations GmbH

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특허 상세정보

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Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/00 G05D-001/00
미국특허분류(USC)	244/194; 244/099.9
출원번호	US-0086467 (2006-12-08)
등록번호	US-8256718 (2012-09-04)
우선권정보	DE-10 2005 059 369 (2005-12-13)
국제출원번호	PCT/EP2006/011867 (2006-12-08)
§371/§102 date	20091027 (20091027)
국제공개번호	WO2007/068413 (2007-06-21)
발명자 / 주소	Fleddermann, Andreas Hartwig, Wolfgang Darbois, Alexandre Richter, Martin
출원인 / 주소	Airbus Operations GmbH
대리인 / 주소	Lerner, David, Littenberg, Krumholz & Mentlik, LLP
인용정보	피인용 횟수 : 3 인용 특허 : 8

초록
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A method and a device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft when a blockage occurs, wherein in response to a control signal emitted by a control device at least one high lift surface, which is actuated by means of a local mechanical final control element, is brought to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement. If a signal is registered that indicates that there is a blockage within the high lift surface system, the torque transmitted by the central drive unit to the rotary shaft arrangement is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.

대표
청구항
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1. A method for providing automatic load alleviation to a landing flap system of an aircraft when a blockage occurs, comprising: in response to a first control signal emitted by a control device bringing at least one high lift surface, which is actuated by means of a local mechanical final control element, to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement, andwherein, if a first signal is registered that indicates that there is a blockage within the high lift surface system, automatically reducing the torque transmitted by the central drive unit to the rotary shaft arrangement to a predetermined low torque value, and fixing the position of the high lift surface system;wherein the first signal that indicates a blockage is derived from registering a second signal which represents a predetermined high torque value in relation to the torque transmitted by the central drive unit to the rotary shaft arrangement in conjunction with an occurrence of a second control signal caused by the pilot to the effect of initiating a reversal in the direction of rotation of the rotary shaft arrangement. 2. The method of claim 1, wherein the first signal that indicates a blockage is derived from registering a third signal that represents a predetermined high torque value in relation to the torque transmitted by the central drive unit to the rotary shaft arrangement for a predetermined period of time. 3. The method of claim 2, wherein the occurrence of the maximum pivoting-disc angle of a hydraulic inclined-axis motor contained in the central drive unit is registered as the third signal that represents the predetermined high torque value. 4. The method of claim 2, wherein the occurrence of the maximum motor current of an electric motor contained in the central drive unit is registered as the third signal that represents the predetermined high torque value. 5. The method of claim 1, wherein the first signal that indicates a blockage is derived from a comparison of a first plurality of signals emitted by position sensors provided in the high lift surface system, which first plurality of signals represents the actual position of the high lift surfaces, with a second plurality of signals predetermined by an evaluation algorithm carried out in the control device, which second plurality of signals represents the command position of the high lift surfaces. 6. The method of claim 5, wherein the first plurality of signals that represents the actual position of the high lift surfaces is obtained by asymmetry position sensors being provided on the ends of the rotary shaft arrangements. 7. The method of claim 1, wherein the predetermined low torque value relating to the torque transmitted by the central drive unit to the rotary shaft arrangement, at which torque the position of the high lift surface system is fixed, is set such that the high lift surfaces are secured against any uncontrolled retraction due to external air loads. 8. The method of claim 1, wherein the predetermined low torque value is set such that it is below the triggering value of a torque limiter that is contained in the rotary shaft arrangement of the high lift surface system. 9. The method of claim 1, wherein fixing the position of the high lift surface system takes place by activating a motor locking brake contained in the central drive unit. 10. The method of claim 1, wherein, after registering the first signal that indicates that there is a blockage, a request is issued to the pilot to issue the second control signal that causes a reversal in the direction of rotation of the rotary shaft arrangement. 11. A device for providing automatic load alleviation to a landing flap system of an aircraft when a blockage occurs, comprising: a control device for emitting a first control signal;a central drive unit;a local mechanical final control element adjustable by the central drive, in response to the control signal, wherein the central drive is connected by way of a rotary shaft arrangement to the final control element; anda braking device,at least one high lift surface actuated by the local mechanical final control element by a torque transmitted by the central drive unit to the rotary shaft arrangement,wherein the control device is configured, when a first signal is registered that indicates that there is a blockage within the high lift surface system, to emit a second signal to the central drive unit, which second signal automatically causes the central drive unit to reduce the torque transmitted by the central drive unit to the rotary shaft arrangement to a predetermined low torque value, and to emit a third signal to the braking device, which third signal fixes the position of the high lift surface system; andwherein the control device is configured for evaluating a fourth signal, which represents a predetermined high torque value in relation to the torque transmitted by the central drive unit to the rotary shaft arrangement in conjunction with the occurrence of a second control signal caused by the pilot to the effect of initiating a reversal in the direction of rotation of the rotary shaft arrangement for deriving the signal that indicates a blockage. 12. The device of claim 11, wherein the control device is configured for evaluating a third signal, which has been registered for a predetermined period of time, and represents a predetermined high torque value in relation to the torque transmitted by the central drive unit to the rotary shaft arrangement as the first signal that indicates a blockage. 13. The device of claim 12, wherein registering the occurrence of the maximum pivoting-disc angle of a hydraulic inclined-axis motor contained in the central drive unit is provided as the third signal that represents the predetermined high torque value. 14. The device of claim 12, wherein registering the occurrence of the maximum motor current of an electric motor contained in the central drive unit is provided as the third signal that represents the predetermined high torque value. 15. The device of claim 11, wherein the control device is configured for deriving the first signal that indicates that there is a blockage by a comparison of a first plurality of signals emitted by position sensors provided in the high lift surface system, which first plurality of signals represents the actual position of the high lift surfaces, with a second plurality of signals predetermined by an evaluation algorithm carried out in the control device, which second plurality of signals represents the command position of the high lift surfaces. 16. The device of claim 15, wherein the first plurality of signals that represents the actual position of the high lift surfaces is obtained from asymmetry position sensors being provided on the ends of the rotary shaft arrangements. 17. The device of claim 11, wherein the predetermined low torque value relating to the torque transmitted by the central drive unit to the rotary shaft arrangement, at which torque the position of the high lift surface system is fixed, is set such that the high lift surfaces are secured against any uncontrolled retraction due to external air loads. 18. The device of claim 11, wherein the predetermined low torque value is set such that it is below the triggering value of a torque limiter that is contained in the rotary shaft arrangement of the high lift surface system. 19. The device of claim 11, wherein a motor locking brake contained in the central drive unit is provided for fixing the position of the high lift surface system. 20. The device of claim 11, wherein the control device is configured , after registering the first signal that indicates that there is a blockage, to emit to the pilot a request to issue the second control signal that causes a reversal in the direction of rotation of the rotary shaft arrangement.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 3

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특허 상세정보

Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft

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Method and device for providing automatic load alleviation to a high lift surface system, in particular to a landing flap system, of an aircraft

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이 특허에 인용된 특허 (8)

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IPC 상세정보(version : 201201)

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