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1.发明授权公开(公告)号：US10449733B2
公开(公告)日：2019-10-22
申请号：US14890923
申请日：2013-05-17
摘要： Methods of making single piece multi-spar boxes made of composite material for aircraft are provided. Such methods include providing outer spars of the boxes which are made with a C-shaped cross-section such that the spars, during curing, are molded on the inside onto rigid, outer, lateral forming tools. As a result it is possible to obtain very precise outer profiles and positions of the spars.
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公开(公告)号：US09878505B2
公开(公告)日：2018-01-30
申请号：US14567584
申请日：2014-12-11
IPC分类号： B29C65/00 , B29C70/54 , B29C33/76 , B29D99/00 , B29C70/30 , B25B11/00 , B29C70/32 , B29L31/00
CPC分类号： B29C70/543 , B25B11/005 , B29C33/76 , B29C70/30 , B29C70/32 , B29D99/0003 , B29L2031/003 , B29L2031/772
摘要： A tool for forming a C-section beam made of carbon fiber includes a straight elongated mandrel with a rectangular or trapezoidal cross-section. The mandrel has three consecutive outer faces, with a planar face configured to form a surface of the web of the C-section beam, and two opposing lateral faces, configured to form two respective surfaces of the flanges of the C-section beam. The mandrel has a distributed perforation on at least one of the three outer faces and an inlet/outlet connection to connect the mandrel to an external source of vacuum and/or compressed air. Passages are formed inside the mandrel to establish a fluid communication between the distributed perforation and the inlet/outlet connection. Through the distributed perforation, a vacuum is applied to the interface between the mandrel and the C-section beam to retain the C-section beam on the mandrel while lifted and turned by 180° for coupling to a similar C-section beam to assemble an H-beam. Applying compressed air through the perforation facilitates the removal of the C-section beam from the mandrel at the end of the compaction step.
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3.发明授权公开(公告)号：US09038686B2
公开(公告)日：2015-05-26
申请号：US13853133
申请日：2013-03-29
发明人： Guido Sibona , Ettore Mostarda , Giuseppe Iovine
CPC分类号： B29D99/001 , B29C53/824 , B64C2001/0072 , Y02T50/43
摘要： Positioning system of sectors of a device for producing an airplane fuselage in which a lamination mandrel comprises a plurality of sectors borne by a supporting structure and mobile along guides between: an expanded lamination position and a contracted disassembling position. Each guide comprises a fixed part borne by the supporting structure and a mobile part sliding along/with respect to the fixed part in a rectilinear direction H. Between a portion of each mobile part facing towards the respective sector and a stiffening structure of the sector a positioning device is provided which allows adjustment of the position of the sector with respect to the guide in two directions which lie in a plane RP perpendicular to the axis H of the guide.
摘要翻译： 用于生产飞机机身的装置的扇区的定位系统，其中层压心轴包括由支撑结构承载的多个扇区，并且可沿着在膨胀的层压位置和收缩的拆卸位置之间的引导移动。 每个引导件包括由支撑结构承载的固定部分和沿着直线方向H相对于固定部分滑动的可移动部件。在每个可移动部件的面向相应扇区的部分和扇形部分a的加强结构之间 提供了一种定位装置，其允许相对于引导件在垂直于引导件的轴线H的平面RP中的两个方向上调整扇形部分的位置。
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4.发明申请公开(公告)号：US20150122413A1
公开(公告)日：2015-05-07
申请号：US14394005
申请日：2013-04-12
CPC分类号： B32B37/1018 , B29C33/485 , B29C70/32 , B29C70/446 , B29L2031/3082 , B32B37/0046 , B32B2309/68 , B32B2605/18 , B64C1/068 , B64C2001/0072 , B64F5/10 , B64F5/50 , Y02T50/43
摘要： A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel with radially retractable sectors (11a, 11b) having parallel longitudinal slots (17) with composite stringers (30) in the slots (17). An inner support (31) in each stringer is covered by an impermeable tubular bag (32). A composite skin (37) is laminated around the stringers (30), the coated supports (31, 32) and the inner forming surface (IML). An outer curing tool (50, 51) closes around the skin (37) defining an fuselage barrel outer forming surface (OML), leaving an annular gap (G) between the skin outer surface (37) and the outer forming surface (OML). Vacuum is applied between the vacuum bag (18) and the outer tool (50, 51), enlarges the uncured barrel diameter, releasing the barrel from the inner mandrel (10) and bringing the skin outer surface (37) into contact with the outer tool inner surface (IML).
摘要翻译： 真空袋（18）围绕内心轴的内成形表面（IML）放置，具有在狭槽（17）中具有带有复合纵梁（30）的平行纵向槽（17）的径向可缩回的扇形区（11a，11b）。 每个纵梁中的内部支撑件（31）被不透水的管状袋（32）覆盖。 复合皮肤（37）层叠在桁条（30），涂覆的支撑件（31,32）和内部成形表面（IML）周围。 外固化工具（50,51）围绕限定机身筒外成形表面（OML）的皮肤（37）闭合，在皮肤外表面（37）和外成形表面（OML）之间留下环形间隙（G） 。 在真空袋（18）和外部工具（50,51）之间施加真空，扩大未固化的桶直径，将筒从内心轴（10）释放并使皮肤外表面（37）与外部接触 工具内表面（IML）。
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5.发明申请DUAL-PHASE FLUID HEATING/COOLING CIRCUIT PROVIDED WITH TEMPERATURE-SENSING FLOW CONTROL VALVES 审中-公开提供温度感应流量控制阀的双相流体加热/冷却电路公开(公告)号：US20150114607A1
公开(公告)日：2015-04-30
申请号：US14526015
申请日：2014-10-28
发明人： Antonio MOSCATELLI
IPC分类号： F28D15/04
CPC分类号： F28D15/043 , F28D15/0266 , F28D15/06
摘要： A circuit includes an evaporator receiving heat from a hot body; a condenser transmits heat to a cold body, a working fluid flows through a first conduit in vapour phase from the evaporator to the condenser, and flows through a second conduit in liquid phase, from the condenser to the evaporator. A first evaporator portion is in fluid communication with the second conduit and acts as a compensation chamber. A second evaporator portion is in fluid communication with the first conduit and contains the vapour phase. A porous wick moves the working fluid from the first evaporator portion to the second evaporator portion. A first flow controller interrupts or allows flow when fluid temperature in the elevator is respectively lower or higher than a first threshold. A second flow controller interrupts or allows flow when the temperature in the condenser is respectively higher or lower than a second threshold.
摘要翻译： 电路包括从热体接收热量的蒸发器; 冷凝器将热量传递到冷体，工作流体从蒸发器流过第一导管，从蒸发器流到冷凝器，并从液相流经冷凝器至蒸发器的第二导管。 第一蒸发器部分与第二导管流体连通并用作补偿室。 第二蒸发器部分与第一管道流体连通并且包含气相。 多孔芯将工作流体从第一蒸发器部分移动到第二蒸发器部分。 当电梯中的液体温度分别低于或高于第一阈值时，第一流量控制器中断或允许流动。 当冷凝器中的温度分别高于或低于第二阈值时，第二流量控制器中断或允许流动。
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6.发明申请METHOD FOR EVALUATING THE STRUCTURAL COMPATIBILITY OF AN AIRCRAFT FOR USE ON ROUGH RUNWAYS 有权用于评估航空器在粗跑道上的结构兼容性的方法公开(公告)号：US20130289803A1
公开(公告)日：2013-10-31
申请号：US13849136
申请日：2013-03-22
IPC分类号： E01C9/00
摘要： A method for evaluating the structural compatibility of an aircraft for use on a runway having a profile with one or more roughnesses in the form of bumps and/or dips, comprising the steps of: generating a first bump height curve representing elevations or depressions on the runway; comparing the bump height curve with a second bump height curve which is a first reference curve; generating a first power spectral density curve of the profile of the runway; comparing the first power spectral density curve with a second power spectral density curve which is a second reference curve; authorizing or denying the aircraft the use of the runway on the basis of results of the comparison between the bump height curve and the first reference curve, and between the power spectral density curve and the second reference curve.
摘要翻译： 一种用于评估在具有凸起和/或凹陷形式的具有一个或多个粗糙度的轮廓的跑道上使用的飞行器的结构兼容性的方法，包括以下步骤：产生表示所述凸起和/或凹陷上的高度或凹陷的第一凸起高度曲线 跑道 将凸起高度曲线与作为第一参考曲线的第二凸起高度曲线进行比较; 产生跑道轮廓的第一功率谱密度曲线; 将第一功率谱密度曲线与作为第二参考曲线的第二功率谱密度曲线进行比较; 根据凸起高度曲线与第一参考曲线之间的比较结果以及功率谱密度曲线与第二参考曲线之间的比较结果，授权或拒绝飞机使用跑道。
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公开(公告)号：US10449734B2
公开(公告)日：2019-10-22
申请号：US14856607
申请日：2015-09-17
发明人： Giuseppe Totaro , Gianni Iagulli
IPC分类号： B29C70/44 , B29C70/34 , B29C33/50 , B29C33/68 , B29D99/00 , B29C65/00 , B64C1/06 , B64C3/18 , B29C65/02 , B29L31/30
摘要： Methods for manufacturing elongated structural elements are provided. Such methods provide composite material having optimal properties such as weight and strength which can be produced at much lower costs compared to conventional methods. Composite materials including such elements are also provided. In addition, commercial products incorporating such structural elements are provided.
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公开(公告)号：US09962917B2
公开(公告)日：2018-05-08
申请号：US14394005
申请日：2013-04-12
IPC分类号： B32B37/10 , B29C70/32 , B29C70/44 , B29C33/48 , B64C1/06 , B32B37/00 , B64F5/10 , B64F5/50 , B29L31/30 , B64C1/00
CPC分类号： B32B37/1018 , B29C33/485 , B29C70/32 , B29C70/446 , B29L2031/3082 , B32B37/0046 , B32B2309/68 , B32B2605/18 , B64C1/068 , B64C2001/0072 , B64F5/10 , B64F5/50 , Y02T50/43
摘要： A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel with radially retractable sectors (11a, 11b) having parallel longitudinal slots (17) with composite stringers (30) in the slots (17). An inner support (31) in each stringer is covered by an impermeable tubular bag (32). A composite skin (37) is laminated around the stringers (30), the coated supports (31, 32) and the inner forming surface (IML). An outer curing tool (50, 51) closes around the skin (37) defining an fuselage barrel outer forming surface (OML), leaving an annular gap (G) between the skin outer surface (37) and the outer forming surface (OML). Vacuum is applied between the vacuum bag (18) and the outer tool (50, 51), enlarges the uncured barrel diameter, releasing the barrel from the inner mandrel (10) and bringing the skin outer surface (37) into contact with the outer tool inner surface (IML).
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公开(公告)号：US20160221692A1
公开(公告)日：2016-08-04
申请号：US15094668
申请日：2016-04-08
发明人： Nicola PIRRO , Michelantonio PINTO
CPC分类号： B64F5/10 , B25B11/02 , Y10T29/49622 , Y10T29/49826
摘要： A method for assembling a first component to at least one second component, includes attaching a plurality of interface fittings to the first component, placing the first component on an assembly jig in such a way that the first component bears on the assembly jig through the interface fittings, and assembling said at least one second component to the first component placed on the assembly jig. Before the first component is placed on the assembly jig, at least one adjustable spacer member incorporated in at least one of said interface fittings is adjusted to bring at least one surface of the first component into a predetermined tolerance range.
摘要翻译： 一种用于将第一部件组装到至少一个第二部件的方法，包括将多个接口配件附接到第一部件，将第一部件放置在组装夹具上，使得第一部件通过接口承载在组装夹具上 配件，并将所述至少一个第二部件组装到放置在组装夹具上的第一部件上。 在将第一部件放置在装配夹具上之前，调节并入至少一个所述接口配件中的至少一个可调整间隔件，以使第一部件的至少一个表面达到预定的公差范围。
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10.发明申请公开(公告)号：US20150367930A1
公开(公告)日：2015-12-24
申请号：US14377795
申请日：2012-12-21
IPC分类号： B64C1/06
CPC分类号： B64C1/069 , B23P19/10 , B64F5/10 , Y10T29/49623 , Y10T29/53061
摘要： An automated system for joining at least two portions of a chassis includes an actuation device (3) adapted to move at least one portion in the space “XYZ” with three degrees of freedom. A central control unit (5) controls each actuation device (3) as a function of data obtained through sensors (7). The sensors (7) can continuously determine, on each chassis portion, key points (A, B, C) which are univocal for each portion. The central control unit (5), depending on data from the sensors (7), activates the actuation device (3) to bring near and connect the at least two portions, while the sensors (7) monitor the relative position between the key points (A, B, C) of the portions and the absolute position of the portions in the space “XYZ”. A method is associated with the automated joining system for automatically joining at least two portions to manufacture a chassis.
摘要翻译： 用于连接底盘的至少两个部分的自动化系统包括适于以三个自由度移动空间“XYZ”中的至少一个部分的致动装置（3）。 中央控制单元（5）根据通过传感器（7）获得的数据来控制每个致动装置（3）。 传感器（7）可以在每个底盘部分上连续地确定对于每个部分是单一的关键点（A，B，C）。 根据来自传感器（7）的数据，中央控制单元（5）启动致动装置（3）以使接近并连接至少两个部分，同时传感器（7）监测关键点之间的相对位置 （A，B，C）和空间“XYZ”中的部分的绝对位置。 一种方法与自动连接系统相关联，用于自动连接至少两个部分以制造底盘。
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