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1. 发明申请

WO2013098666A1 INSERT OF ELECTRICALLY CONDUCTING MATERIAL, AND TOOL AND METHOD FOR FITTING SUCH AN INSERT TO A SUPPORTING MEMBER 审中-公开
标题翻译：电导体材料插件，以及用于将这种插入件配合到支撑构件的工具和方法
公开(公告)号：WO2013098666A1
公开(公告)日：2013-07-04
申请号：PCT/IB2012/055525
申请日：2012-10-11
申请人： AGUSTAWESTLAND S.P.A.
发明人： MARCON, Tiziano , BAROLI, Flavio , BEZZON, Luigi , GUSSONI, Roberto , PURICELLI, Enrico , SOTGIU, Simone
IPC分类号： F16B5/01
CPC分类号： H01R4/304 , F16B5/01 , F16B2001/0064 , H01R4/30 , H01R13/622 , Y10T29/49117 , Y10T29/5313
摘要： An insert (10) made of electrically conducting material, insertable at least partly inside a seat (8) on a first member (2), and connectable to a second member (1); the insert (10) having a fastening member (11) connectable electrically to a first electrically conducting area (4, 7) on the first member (2).
摘要翻译：一种由导电材料制成的插入件（10），其至少部分地可插入在第一构件（2）上的座（8）内并且可连接到第二构件（1）; 所述插入件（10）具有可与所述第一构件（2）上的第一导电区域（4,7）电连接的紧固构件（11）。

2. 发明申请

WO2013098665A1 AIRCRAFT INTERIOR TRIM PANEL, AND AIRCRAFT FITTED WITH SUCH PANELS 审中-公开
标题翻译：飞机内部TRIM面板和飞机与这些面板相连
公开(公告)号：WO2013098665A1
公开(公告)日：2013-07-04
申请号：PCT/IB2012/055523
申请日：2012-10-11
申请人： AGUSTAWESTLAND S.P.A.
发明人： PERAZZOLO, Alessandro , SCAINI, Sara
IPC分类号： B32B3/00 , B64C1/06 , B64C1/40
CPC分类号： B64C1/40 , B32B3/12 , B32B3/266 , B32B5/18 , B32B5/245 , B32B9/025 , B32B9/046 , B32B2260/021 , B32B2260/046 , B32B2266/06 , B32B2307/102 , B32B2307/56 , B32B2307/724 , B32B2307/7242 , B32B2605/003 , B32B2605/18 , B64C1/066 , G10K11/168 , G10K11/172
摘要： A trim panel (10) for the interior (11) of an aircraft (E), the panel having a multilayer structure and including an outer layer (12) made of material impervious to air, and which is positioned in use facing the fuselage of the aircraft (E); an inner layer (13) made of trim material, and which in use defines the interior (11); a structural layer (14) interposed between the inner and outer layer (13, 12); and acoustic energy dissipating material (17, 21), also interposed between the inner (13) and outer (12) layer; the inner layer (13) being made of porous material allowing airflow towards the acoustic energy dissipating material (17, 21).
摘要翻译：一种用于飞行器（E）的内部（11）的装饰板（10），所述面板具有多层结构并且包括由不透空气的材料制成的外层（12），并且其被定位在面向机身的机身飞机（E）; 由修剪材料制成的内层（13），其在使用中限定内部（11）; 介于所述内层和外层之间的结构层（14）; 以及也插入在所述内部（13）和外部（12）层之间的声能消散材料（17,21）; 内层（13）由多孔材料制成，允许气流朝向声能消散材料（17,21）。

3. 发明申请

WO2016020900A1 HELICOPTER ANTI-TORQUE ROTOR 审中-公开
标题翻译：直升机抗扭转子
公开(公告)号：WO2016020900A1
公开(公告)日：2016-02-11
申请号：PCT/IB2015/056031
申请日：2015-08-07
申请人： AGUSTAWESTLAND S.P.A.
发明人： WANG, James
IPC分类号： B64C27/68 , B64C27/78 , B64C27/82
CPC分类号： B64C27/82 , B64C27/54 , B64C27/58 , B64C27/59 , B64C27/68 , B64C27/78
摘要： An anti-torque rotor (4, 4') of a helicopter (1), having : a supporting body (14, 14'); a drive shaft (10, 10') which rotates about a first axis (B) with respect to the supporting body (14, 14'); a hub (11) connected operatively to drive shaft (10, 10') and angularly fixed with respect to first axis (B); at least one blade (12) which is connected operatively to hub (11), is angularly fixed with respect to first axis (B), and is angularly movable with respect to a second axis (D) to adjust the pitch angle of blade (12); and an actuator (16, 16') which can be operated to rotate blade (12) about second axis (D) to adjust the pitch angle of blade (12); actuator (16, 16') has an electric motor (25, 25') which generates torque along the first axis (B); and a mechanical stage (30, 30') interposed between the electric motor (25, 25') and blade (12), and designed to convert the torque into rotation of blade (12) about the respective second axes (D); electric motor (25, 25') is fixed to supporting body (14, 14').
摘要翻译： 1.一种直升机（1）的抗扭矩转子（4,4'），具有：支撑体（14,14'）; 围绕第一轴线（B）相对于支撑体（14,14'）旋转的驱动轴（10,10'）; 枢轴（11），其可操作地连接到驱动轴（10,10'）并相对于第一轴线（B）成角度地固定; 可操作地连接到轮毂（11）的至少一个叶片（12）相对于第一轴线（B）成角度地固定，并且可相对于第二轴线（D）成角度地移动，以调节叶片的俯仰角 12）; 以及致动器（16,16'），其可以被操作以围绕第二轴线（D）旋转叶片（12）以调节叶片（12）的俯仰角; 致动器（16,16'）具有沿着第一轴线（B）产生扭矩的电动机（25,25'）。以及插入在所述电动机（25,25'）和叶片（12）之间的机械平台（30,30'），并被设计成将扭矩转换成围绕相应的第二轴线（D）的叶片（12）的转动; 电动机（25,25'）固定在支撑体（14,14'）上。

4. 发明申请

WO2016009408A1 SEALING RING 审中-公开
标题翻译：密封圈
公开(公告)号：WO2016009408A1
公开(公告)日：2016-01-21
申请号：PCT/IB2015/055442
申请日：2015-07-17
申请人： AGUSTAWESTLAND S.P.A.
发明人： COLOMBO, Dario , GASPARINI, Giuseppe , PISANI, Paolo
IPC分类号： F16J15/34
CPC分类号： F16J15/3412
摘要： A sealing ring (17'') for a seal assembly (6) is described that comprises: a main body (40, 41) rotating about an axis (A); and a first surface (19), which is defined by the main body (40, 41), extends transversely to the axis (A) and is suitable for abutting against a further sealing ring (18) in a direction parallel to the axis (A); the first surface (19) comprises a plurality of grooves (35a'', 35b'') forming respective hydropads; the grooves (35a'', 35b'') are delimited by a first edge (36'') and a second edge (37'') facing one another; the first edge (36'') and the second edge (37'') delimit the grooves (35a'', 35b'') in a circumferential direction to said axis (A); at least one of the first edge (; 36'') and the second edge (37'') is shaped like an elliptical arc, which has coincident or separate foci; comprises first grooves (35a'') and second grooves (35b'') alternating with one another in a circumferential direction to said axis (A) and staggered from each other in a radial direction to said axis (A).
摘要翻译：描述了一种用于密封组件（6）的密封环（17“），其包括：围绕轴线（A）旋转的主体（40,41）; 并且由所述主体（40,41）限定的第一表面（19）横向于所述轴线（A）延伸并且适于在平行于所述轴线的方向上抵靠另一个密封环（18）一个）; 第一表面（19）包括形成相应的水平面的多个凹槽（35a“，35b”）; 凹槽（35a“，”35b“）由第一边缘（36”）和彼此相对的第二边缘（37“）界定; 所述第一边缘（36“）和所述第二边缘（37”）在与所述轴线（A）的圆周方向上限定所述凹槽（35a“，35b”）; 所述第一边缘（; 36“）和所述第二边缘（37”）中的至少一个被成形为类似椭圆弧，其具有重合或分离的焦点; 包括在与所述轴线（A）的圆周方向上彼此交替并且在径向方向上与所述轴线（A）交错的第一凹槽（35a“）和第二凹槽（35b”）。

5. 发明申请

WO2013011470A2 REAL-TIME SIMULATION SYSTEM OF THE EFFECTS OF ROTOR-WAKE GENERATED AERODYNAMIC LOADS OF A HOVER-CAPABLE AIRCRAFT ON THE AIRCRAFT ITSELF, AND METHOD THEREOF 审中-公开
标题翻译：具有霍夫能力的飞机的转子振荡产生的空气负载对飞机本身的影响的实时仿真系统及其方法
公开(公告)号：WO2013011470A2
公开(公告)日：2013-01-24
申请号：PCT/IB2012/053666
申请日：2012-07-18
申请人： AGUSTAWESTLAND S.p.A. , BIANCO MENGOTTI, Riccardo , SCORCELLETTI, Francesco
发明人： BIANCO MENGOTTI, Riccardo , SCORCELLETTI, Francesco
IPC分类号： G09B9/08
CPC分类号： G09B9/46
摘要： A real-time simulation system (1) of the aerodynamic loads generated by the wake of a rotor (2) of a hover-capable aircraft (3) on the aircraft (3) itself is described, said system (1) comprising: a cockpit seat (10) for a pilot; a simulated control device (11) of the aircraft (3) able to receive a simulated command from the pilot to simulate a flight condition of the aircraft (3); simulation means (13) able to generate a simulated representation of the flight condition; and a processing unit (14) configured to receive as input a first signal associated with the command given via the control device (11) and to generate and output a second control signal for the simulation means (13) associated with the simulated aerodynamic loads. The processing unit (14) cyclically generates a vortex ring (30) with a radius (r), associates a number of control points (A, B, C and D) with the vortex ring (30), computes the velocity induced on the control points (A, B, C and D), moves and updates the vortex ring (30), and generates the second signal on the basis of the velocities induced on the control points (A, B, C and D) by the vortex rings (30).
摘要翻译：描述了由飞机（3）自身上的悬停式飞行器（3）的转子（2）的尾迹产生的空气动力负载本身的实时仿真系统（1）所述系统（1）包括：驾驶员座椅（10），用于飞行员; 飞行器（3）的模拟控制装置（11）能够接收来自飞行员的模拟命令以模拟飞行器（3）的飞行状态; 模拟装置（13），其能够生成所述飞行状况的模拟表示; 以及处理单元（14），其被配置为接收与经由所述控制装置（11）给出的所述命令相关联的第一信号作为输入并且生成并输出用于与所述模拟空气动力学负载相关联的所述模拟装置（13）的第二控制信号。处理单元（14）循环地产生具有半径（r）的涡环（30），将多个控制点（A，B，C和D）与涡环（30）相关联，计算在控制点（A，B，C和D）移动并更新涡环（30），并基于由涡旋在控制点（A，B，C和D）上感应的速度产生第二信号戒指（30）。

6. 发明申请

WO2016001901A1 HELICOPTER WITH NOISE AND VIBRATION DAMPING TRANSMISSION MOUNTING 审中-公开
标题翻译：具有噪声和振动阻尼传动装置的直升机
公开(公告)号：WO2016001901A1
公开(公告)日：2016-01-07
申请号：PCT/IB2015/055045
申请日：2015-07-03
申请人： AGUSTAWESTLAND S.P.A.
发明人： BOTTASSO, Luigi Maria , GHIRINGHELLI, Gian Luca , PERAZZOLO, Alessandro , CENEDESE, Fausto
IPC分类号： B64C27/00 , B64C27/12
CPC分类号： B64C27/001 , B64C27/12 , B64C27/82 , B64C2027/002
摘要： A helicopter (1) is described that comprises: a rotor (3); a fuselage (2); a drive transmission unit (7) operatively connected to the rotor (3); a support body (14), which supports the transmission unit (7); and constraining means (21) interposed between the support body (14) and the fuselage (2); the constraining means (21) in turn comprise a crosspiece (21) connected in a fixed manner with respect to the support body (14) and having a first lying plane (P); the crosspiece (21) is formed in part by a metallic material and in part by a visco-elastic material.
摘要翻译：一种直升机（1），其包括：转子（3）; 机身（2）; 可操作地连接到转子（3）的驱动传动单元（7）; 支撑所述传动单元（7）的支撑体（14）; 以及插入在所述支撑体（14）和所述机身（2）之间的约束装置（21）。约束装置（21）又包括相对于支撑体（14）以固定方式连接并且具有第一躺平面（P）的横档（21）; 横档（21）部分地由金属材料形成，部分地由粘弹性材料形成。

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