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1. 发明公开

EP2435308A1 FLUGZEUG MIT EINEM HOCHAUFTRIEBSSYSTEM 有权
标题翻译：与高升力系统PLANE
公开(公告)号：EP2435308A1
公开(公告)日：2012-04-04
申请号：EP10722624.3
申请日：2010-05-26
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin , LÜCKEN, Peter
IPC分类号： B64D45/00 , B64C13/50
CPC分类号： B64C13/503 , B64D45/0005 , B64D2045/001
摘要： The invention relates to an aircraft having a vertical lift system, comprising: at least one flight control computer (51), vertical lifting bodies each disposed on one airfoil of the aircraft, a drive device coupled to said bodies, an actuating device connected to the drive device by means of an analog data connection for generating actuating commands for adjusting the adjustment state of the vertical lifting bodies, an input device disposed in the cockpit of the aircraft for inputting target commands for adjusting the vertical lifting bodies, and sensors for capturing an adjustment state of the vertical lifting bodies and connected to the actuating device by means of analog signal lines. According to the invention, the input device is connected by means of a digital data connection to the actuation device for determining the target commands for adjusting the vertical lifting body. According to the invention, the actuating device is installed in the cargo load area of the aircraft fuselage, and in an area (L3) extending from a point having a distance ((L1)/3) of one-third of the fuselage length extending from there to the nose of the aircraft (F1) as seen from the front side (F4-1) of the wing frame (F4), to a point having a distance ((L2)/3) of one-third of the fuselage length (L2) extending from there to the end of the fuselage (F2) at the tail of the aircraft (F) as seen from the rear side (F4-2) of the wing frame (F4).

2. 发明公开

EP2328806A1 FEHLERTOLERANTES STELLSYSTEM ZUR VERSTELLUNG VON KLAPPEN EINES FLUGZEUGS MIT EINER VERSTELL-KINEMATIK MIT FESTSTEHENDER DREHACHSE 有权
标题翻译：容错停车系统平差使用具有固定旋转轴和方法襟翼调节运动的飞行器来监视停车场系统
公开(公告)号：EP2328806A1
公开(公告)日：2011-06-08
申请号：EP09741872.7
申请日：2009-05-05
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin , FLEDDERMANN, Andreas
IPC分类号： B64C13/24 , B64D45/00
CPC分类号： B64D45/0005 , B64C13/42 , B64D2045/001 , Y02T50/44
摘要： The invention relates to an error tolerant adjustment system comprising at least one servo tab (A1, A2; B1, B2) that can be adjusted on respectively one of the carrier wings of an aircraft and comprising a control and monitoring device (5). Said adjustment system comprises drive devices (PA1, PA2, PB1, PB2) that are functionally connected to the adjusting and monitoring device (5), each drive device being associated with each servo tab (A1, A2; B1, B2), and each drive device respectively comprising two drive motors (M1, M2), two braking devices (B1, B2), each braking device (B1, B2) being associated with each drive motor (M1, M2) and being used to block the output of the respective drive motor (M1, M2), a differential couples the outputs of each motor is such a manner that they are accumulated, an output shaft for coupling the output of the differential to drive connections (51, 52) and a differential lock (D) that is functionally connected to the control and monitoring device (5), said lock being coupled to the control and monitoring device (5) in such a manner that each braking device (B1, B2) and the differential lock (50) can be actuated by a command signal of the control and monitoring device (5); and adjusting devices (A11, A12, A21, A22; B11, B12, B21, B22) to which the drive device (PA1, PA2, PB1, PB2) associated with the servo tabs (A1, A2; B1, B2) is coupled, each adjusting device comprising a transmission gearing (20), an adjusting mechanism (21) and a position sensor (22) that is functionally connected to the control and monitoring device (5) for determining the adjusting state of the servo tab; the control and monitoring device (5) comprises a control function for controlling command signals for the drive motors (M1, M2) for adjusting the servo tab.

3. 发明授权

EP1960263B1 METHOD AND DEVICE FOR PROVIDING AUTOMATIC LOAD ALLEVIATION TO A HIGH LIFT SURFACE SYSTEM, IN PARTICULAR TO A LANDING FLAP SYSTEM, OF AN AIRCRAFT 有权
标题翻译：方法和设备，用于使自动负载放缓高升力区系统，特别是在飞机着陆襟翼系统
公开(公告)号：EP1960263B1
公开(公告)日：2011-03-16
申请号：EP06829459.4
申请日：2006-12-08
申请人： Airbus Operations GmbH
发明人： FLEDDERMANN, Andreas , HARTWIG, Wolfgang , DARBOIS, Alexandre , RICHTER, Martin
IPC分类号： B64C13/24 , B64D45/00 , G05D1/00
CPC分类号： B64C13/16
摘要： Described are 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 (31, 32, 35) at least one high lift surface (11, 12, 21), which is actuated by means of a local mechanical final control element (16, 26), is brought to a predetermined position by a central drive unit (13, 23) that is connected by way of a rotary shaft arrangement (15, 25) to the local final control element (16, 26) by means of generating a torque transmitted by the central drive unit (13, 23) to the rotary shaft arrangement (15, 25). According to the invention, 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 (13, 23) to the rotary shaft arrangement (15, 25) is automatically reduced to a predetermined low torque value, and the position of the high lift surface system is fixed.

4. 发明公开

EP2625104A1 HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH A SEPARATE DRIVE UNIT FOR EACH WING HALF 有权
标题翻译： HOCHAUFTRIEBSSYSTEMFÜREIN FLUGZEUG MIT SEPARATER ANTRIEBSEINHEITFÜRJEDETRAGFLÄCHENHÄLFTE
公开(公告)号：EP2625104A1
公开(公告)日：2013-08-14
申请号：EP11764226.4
申请日：2011-10-05
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin
IPC分类号： B64D45/00 , B64C13/30
CPC分类号： B64C13/28 , B64C13/30 , B64D45/0005 , B64D2045/001 , Y02T50/44
摘要： A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.
摘要翻译：提供飞机机翼上的高升程系统。机翼包括右手和左手翼半部，其具有可移动地保持的高提升襟翼，右侧和左侧翼半部附接到飞行器机身，从而形成翼根。在靠近翼根的区域中的每个翼半部包括驱动单元。在每种情况下，该驱动单元连接到机械地连接到相应驱动单元的传动轴，该传动轴从驱动单元沿着相应的翼半部的端部的方向延伸，并被设计成机械地移动高升降翼布置在相应的翼半部。通过这种布置，可以在没有偏转齿轮装置的情况下从中心驱动单元到单独的翼片半部进行。

5. 发明授权

EP2328806B1 FEHLERTOLERANTES STELLSYSTEM ZUR VERSTELLUNG VON KLAPPEN EINES FLUGZEUGS MIT EINER VERSTELLKINEMATIK MIT FESTSTEHENDER DREHACHSE SOWIE VERFAHREN ZUR ÜBERWACHUNG EINES STELLSYSTEMS 有权
标题翻译：容错停车系统平差使用具有固定旋转轴和方法襟翼调节运动的飞行器来监视停车场系统
公开(公告)号：EP2328806B1
公开(公告)日：2012-09-19
申请号：EP09741872.7
申请日：2009-05-05
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin , FLEDDERMANN, Andreas
IPC分类号： B64C13/42
CPC分类号： B64D45/0005 , B64C13/42 , B64D2045/001 , Y02T50/44

6. 发明授权

EP2625104B1 HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH A SEPARATE DRIVE UNIT FOR EACH WING HALF 有权
标题翻译：高升降系统用于每个半侧带有单独驱动单元的飞机
公开(公告)号：EP2625104B1
公开(公告)日：2017-07-19
申请号：EP11764226.4
申请日：2011-10-05
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin
IPC分类号： B64D45/00 , B64C13/30
CPC分类号： B64C13/28 , B64C13/30 , B64D45/0005 , B64D2045/001 , Y02T50/44
摘要： A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves.
摘要翻译：提供飞机机翼上的高升力系统。机翼包括一个右翼和一个左翼翼，一半带有可移动的高升力襟翼，右翼和左翼一半连接在飞机机身上，从而形成翼根。靠近翼根的区域中的每个翼半部包括驱动单元。在每种情况下，该驱动单元与机械地连接到相应的驱动单元的传动轴连接，该传动轴从驱动单元沿着相应的机翼半部的端部的方向延伸并且被设计成机械地移动高升力襟翼布置在相应的翼半部中。通过这种布置，可以在没有从中央驱动单元到各个半翼的偏转齿轮装置的情况下进行。

7. 发明授权

EP2435308B1 FLUGZEUG MIT EINEM HOCHAUFTRIEBSSYSTEM 有权
标题翻译：与高升力系统PLANE
公开(公告)号：EP2435308B1
公开(公告)日：2016-11-23
申请号：EP10722624.3
申请日：2010-05-26
申请人： Airbus Operations GmbH
发明人： RICHTER, Martin , LÜCKEN, Peter
IPC分类号： B64D45/00 , B64C13/50
CPC分类号： B64C13/503 , B64D45/0005 , B64D2045/001

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