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公开(公告)号：EP2746118B1
公开(公告)日：2018-05-16
申请号：EP13196124.5
申请日：2013-12-06
发明人： Vaney, Jean-Baptiste , Frank, David , Lemay, David
CPC分类号： B60T8/1703 , B60T7/042 , B60T8/00 , B60T8/26 , B60T17/221 , B64C25/445
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公开(公告)号：EP3036157B1
公开(公告)日：2017-08-30
申请号：EP14742342.0
申请日：2014-07-21
发明人： MORRIS, James , COLOSIMO, Antonio
CPC分类号： B64C25/445 , B60T8/00 , B60T8/1703 , B64C25/34 , B64C25/405 , Y02T50/823
摘要： The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
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公开(公告)号：EP2746118A1
公开(公告)日：2014-06-25
申请号：EP13196124.5
申请日：2013-12-06
发明人： Vaney, Jean-Baptiste , Frank, David , Lemay, David
CPC分类号： B60T8/1703 , B60T7/042 , B60T8/00 , B60T8/26 , B60T17/221 , B64C25/445
摘要： L'invention concerne un procédé de gestion du freinage d'un aéronef comportant une pluralité de roues R1, ..., R12 équipées chacune d'un frein F1, ..., F12 adapté à générer un effort de freinage en réponse à un enfoncement de pédales 5 de frein, le procédé de gestion comprenant les étapes de :
- répartir les roues équipées d'un frein en au moins deux groupes distincts G1, G2, G3, G'1, G'2, G'3 ;
- affecter à chaque groupe de roues des lois de freinage respectives de variation de l'effort de freinage en fonction de l'enfoncement des pédales de frein ;
- permuter à intervalles prédéterminés l'affectation des lois aux groupes selon une loi de permutation prédéfinie.
Selon l'invention, le procédé comporte en outre l'étape de modifier la loi de permutation en réponse à la survenue d'un évènement prédéterminé.摘要翻译： 该方法包括将配备有制动器的一组轮分配到两个不同的组（G1-G3，G'1-G'3）中。 根据一组制动踏板的下压，将一组关于制动力变化的制动规律分配给该组车轮组中的每一组。 根据预设排列规律，以规定的时间间隔对组进行分配。 响应于预定事件的发生修改排列定律。
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公开(公告)号：EP3243746A1
公开(公告)日：2017-11-15
申请号：EP17175816.2
申请日：2014-07-21
发明人： MORRIS, James , COLOSIMO, Antonio
CPC分类号： B64C25/445 , B60T8/00 , B60T8/1703 , B64C25/34 , B64C25/405 , Y02T50/823
摘要： The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
摘要翻译： 本发明提供了用于在自主推回动作期间，即在没有推回拖拉机的情况下在飞机自身动力下控制飞机速度的方法和系统。 该方法包括向飞机的至少一个起落架轮施加转矩，该转矩的方向与起落架轮的向后滚动旋转方向相反。 施加的扭矩不超过确保飞机纵向稳定性的限制。 对于纵向稳定性，所施加的扭矩不应导致飞机冒险发生翻倒事件。
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5.发明公开MEASURING LOAD, DISPLACEMENT ON AN AIRCRAFT COMPONENT USING A MICROWAVE BEAM 审中-公开测量负荷，SHIFT在一个平面上 - 部分配备了微波炉 - RAY
公开(公告)号：EP1664707A1
公开(公告)日：2006-06-07
申请号：EP04768220.8
申请日：2004-08-26
申请人： Airbus UK Limited
CPC分类号： G01L5/00 , B64C25/001 , B64C25/445 , B64C25/46 , B64C25/58 , G01L1/25
摘要： The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit (6, 10, 11), a controllable microwave emitter (2) of electromagnetic radiation and a microwave detector (3) comprising a plurality of antennae (3a, 3b). When the aircraft component is subjected to a load relative movement of the emitter (2) and detector (3) is caused. The detector (3) generates in response to microwave radiation received from the focused beam (8) of radiation emitted by the emitter (2) a signal that is received by a signal processor (10, 11) of the control unit. The signal received by the control unit depends on the relative positions of the emitter (2) and detector (3). The control unit is arranged to provide an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximise braking efficiency without overloading the landing gear leg. 10 Ghr, 50 mm, 0.1 mm.
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公开(公告)号：EP3036157A1
公开(公告)日：2016-06-29
申请号：EP14742342.0
申请日：2014-07-21
发明人： MORRIS, James , COLOSIMO, Antonio
CPC分类号： B64C25/445 , B60T8/00 , B60T8/1703 , B64C25/34 , B64C25/405 , Y02T50/823
摘要： The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
摘要翻译： 本发明提供了用于在自主推回机动中控制飞行器速度的方法和系统，即在没有推回式拖拉机的情况下在飞行器自身的功率下。 该方法包括向飞行器的至少一个起落架轮施加扭矩，扭矩处于与起落架的向后滚动方向相反的方向。 施加的扭矩不超过确保飞机纵向稳定性的极限。 对于纵向稳定性，施加的扭矩不应导致飞机冒险倾倒事故。
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7.发明公开MEASURING LOAD ON AN AIRCRAFT COMPONENT BY MICROWAVE DISTANCE LINKS 审中-公开最后的措施在一个平面上COMPONENT微波长距离连接
公开(公告)号：EP1660853A1
公开(公告)日：2006-05-31
申请号：EP04768217.4
申请日：2004-08-26
申请人： Airbus UK Limited
CPC分类号： B64C25/58 , B60T8/325 , B60T8/52 , B64C25/001 , B64C25/445 , B64C25/46 , G01L1/25
摘要： The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a processing unit, a plurality of controllable microwave emitters (1) of electromagnetic radiation including a pulsed time-coded signal (PTCS) and a microwave detector (3) comprising a plurality of antennae. When the aircraft component is subjected to a load relative movement of the emitter (1) and detector (3) is caused. The antennae of the detector (3) generate in response to microwave radiation received from PTCS emitted by the emitter (1) signals that are received by a signal processor (7) of the processing unit. The timing of the signals received by the processing unit depends on the relative positions of the emitter (1) and detector (3). With the use of triangulation techniques, the processing unit provides an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximise braking efficiency without overloading the landing gear leg.
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