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公开(公告)号：US08740133B2
公开(公告)日：2014-06-03
申请号：US13055340
申请日：2009-07-21
IPC分类号： B64C1/40
CPC分类号： B64D31/12 , B64C11/008 , B64C11/48 , B64C11/50 , B64D27/08 , B64D2027/026 , Y02T50/66
摘要： An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.
摘要翻译： 一种包括至少一个具有反转转子的发动机的发动机，所述发动机或至少一个所述发动机具有与至少一个椭圆相关联的不平衡。 飞行器包括至少一个振动阻尼器，该振动阻尼器以一种布置方式附接，使得在给定的发动机转速下，对于椭圆的大轴或至少一个椭圆的至少一个给定的共同方向，与两端相关的速度 的阻尼器比阻尼器的任何其它布置高。
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2.发明申请公开(公告)号：US20110198440A1
公开(公告)日：2011-08-18
申请号：US13055305
申请日：2009-07-21
CPC分类号： B64D31/12
摘要： The aircraft includes at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes a means capable of controlling the engine or at least one of the engines such that, at a given engine speed, the large axis of the ellipse or at least one of the ellipses extends in a direction for which the vibrations generated by the engine or engines have a minimum intensity in at least one predetermined site, particularly in a predetermined area, of the aircraft.
摘要翻译： 该飞行器包括至少一个具有反向旋转转子的发动机，发动机或至少一个发动机具有与至少一个椭圆相关联的不平衡。 飞行器包括能够控制发动机或发动机中的至少一个的装置，使得在给定的发动机转速下，椭圆的大轴或椭圆中的至少一个沿着由其产生的振动的方向延伸 发动机或发动机在飞行器的至少一个预定位置，特别是在预定区域中具有最小强度。
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公开(公告)号：US20110189017A1
公开(公告)日：2011-08-04
申请号：US13055340
申请日：2009-07-21
CPC分类号： B64D31/12 , B64C11/008 , B64C11/48 , B64C11/50 , B64D27/08 , B64D2027/026 , Y02T50/66
摘要： An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.
摘要翻译： 一种包括至少一个具有反转转子的发动机的发动机，所述发动机或至少一个所述发动机具有与至少一个椭圆相关联的不平衡。 飞行器包括至少一个振动阻尼器，该振动阻尼器以一种布置方式附接，使得在给定的发动机转速下，对于椭圆的大轴或至少一个椭圆的至少一个给定的共同方向，与两端相关的速度 的阻尼器比阻尼器的任何其它布置高。
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4.发明授权公开(公告)号：US09085372B2
公开(公告)日：2015-07-21
申请号：US13055305
申请日：2009-07-21
IPC分类号： B64D31/12
CPC分类号： B64D31/12
摘要： The aircraft includes at least one engine having contra-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes a means capable of controlling the engine or at least one of the engines such that, at a given engine speed, the large axis of the ellipse or at least one of the ellipses extends in a direction for which the vibrations generated by the engine or engines have a minimum intensity in at least one predetermined site, particularly in a predetermined area, of the aircraft.
摘要翻译： 该飞行器包括至少一个具有反转转子的发动机，发动机或至少一个发动机具有与至少一个椭圆相关联的不平衡。 飞行器包括能够控制发动机或发动机中的至少一个的装置，使得在给定的发动机转速下，椭圆的大轴或椭圆中的至少一个沿着由其产生的振动的方向延伸 发动机或发动机在飞行器的至少一个预定位置，特别是在预定区域中具有最小强度。
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5.发明申请REAR PART OF AN AIRCRAFT INCLUDING AN ENGINE SUPPORT STRUCTURE ASSEMBLED SO AS TO OSCILLATE ON THE FUSELAGE 有权航空器的后部分包括发动机支撑结构，因此要摆放在FUSELAGE上公开(公告)号：US20120006937A1
公开(公告)日：2012-01-12
申请号：US13257628
申请日：2010-03-29
申请人： Laurent Lafont , Jean-Michel Saucray , Esteban Quiroz-Hernandez , Jerome Antypas , Mathieu Bonnet , Frederic Journade
发明人： Laurent Lafont , Jean-Michel Saucray , Esteban Quiroz-Hernandez , Jerome Antypas , Mathieu Bonnet , Frederic Journade
摘要： A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.
摘要翻译： 飞行器的后部包括对称地位于中间垂直平面的任一侧上的两个连杆，其中每个连杆具有安装在发动机的支撑结构上的端部和安装在机身上的另一端，其中该部件被配置为 允许连接杆围绕其旋转轴线旋转，由支撑结构和发动机相对于机身通过第一和第二机身开口形成的有限振幅的振动运动。
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6.发明授权Rear part of an aircraft including an engine support structure assembled so as to oscillate on the fuselage 有权飞机的后部包括组装成在机身上振荡的发动机支撑结构公开(公告)号：US08480025B2
公开(公告)日：2013-07-09
申请号：US13257628
申请日：2010-03-29
申请人： Laurent Lafont , Jean-Michel Saucray , Esteban Quiroz-Hernandez , Jerome Antypas , Mathieu Bonnet , Frederic Journade
发明人： Laurent Lafont , Jean-Michel Saucray , Esteban Quiroz-Hernandez , Jerome Antypas , Mathieu Bonnet , Frederic Journade
IPC分类号： B64D27/00
摘要： A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.
摘要翻译： 飞行器的后部包括对称地位于中间垂直平面的任一侧上的两个连杆，其中每个连杆具有安装在发动机的支撑结构上的端部和安装在机身上的另一端，其中该部件被配置为 允许连接杆围绕其旋转轴线旋转，由支撑结构和发动机相对于机身通过第一和第二机身开口形成的有限振幅的振动运动。
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公开(公告)号：US08517304B2
公开(公告)日：2013-08-27
申请号：US12894726
申请日：2010-09-30
IPC分类号： B64D27/26
CPC分类号： B64D27/12 , B64C11/48 , B64D2027/026 , B64D2027/264 , Y02T50/66
摘要： A device for locking an engine on a pylon includes two systems attaching the engine to the pylon, located in attachment regions spaced out in a longitudinal direction of the engine. A second region is adjacent to a center of gravity plane of the engine and closer to a fan than a first region. A first system attaching to the first region is rigid towards torsional, transverse and vertical engine forces. The first region is located at a separation between two compressors of the engine or two turbines, whether the fan is at a rear or front of the engine respectively, the separation being adjacent to a node of a first engine flexural mode. A second system attaching to the second region is rigid towards transverse and vertical forces but less rigid than the first system. The device also includes a third system withstanding thrust forces in the longitudinal direction.
摘要翻译： 用于将发动机锁定在挂架上的装置包括将发动机附接到塔架的两个系统，所述塔架位于沿发动机的纵向间隔开的附接区域中。 第二区域与发动机的重心平面相邻，并且比第一区域更靠近风扇。 附接到第一区域的第一系统对于扭转，横向和垂直的发动机力是刚性的。 第一区域位于发动机的两个压缩机或两个涡轮机之间的分离处，无论风扇是分别位于发动机的后部还是前部，分离器与第一发动机弯曲模式的节点相邻。 附接到第二区域的第二系统对于横向和垂直力是刚性的，但是比第一系统刚性小。 该装置还包括在纵向上承受推力的第三系统。
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