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公开(公告)号：EP2889123B1
公开(公告)日：2020-03-18
申请号：EP14193499.2
申请日：2014-11-17
发明人： Räckers, Bernd , Gerber, Martin
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公开(公告)号：EP2886453B1
公开(公告)日：2019-06-12
申请号：EP13198176.3
申请日：2013-12-18
发明人： Gerber, Martin
IPC分类号： B64C21/06
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公开(公告)号：EP2955108B1
公开(公告)日：2018-02-21
申请号：EP14172381.7
申请日：2014-06-13
发明人： Gerber, Martin
IPC分类号： B64C21/06
CPC分类号： B64C21/06 , B64C5/06 , B64C2230/04 , B64C2230/20 , B64C2230/22 , Y02T50/166
摘要： Aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on the front portion of the vertical stabilizer an elongated one-piece nose element (20) is mounted which forms lateral air guide surfaces, and to the front end of the nose element (20) a perforated metal plate nose member (25) is attached, and wherein the front end of the nose element (20) is closed and between this closed front end and the nose member (25) an elongated air channel (9) is formed.
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公开(公告)号：EP2955108A1
公开(公告)日：2015-12-16
申请号：EP14172381.7
申请日：2014-06-13
发明人： Gerber, Martin
IPC分类号： B64C21/06
CPC分类号： B64C5/02 , B64C21/06 , B64C2230/04 , B64C2230/20 , B64C2230/22 , Y02T50/166
摘要： Aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on the front portion of the vertical stabilizer an elongated one-piece nose element (20) is mounted which forms lateral air guide surfaces, and to the front end of the nose element (20) a perforated metal plate nose member (25) is attached, and wherein the front end of the nose element (20) is closed and between this closed front end and the nose member (25) an elongated air channel (9) is formed.
摘要翻译： 具有机身，机翼，水平稳定器和垂直稳定器的飞行器，其中在垂直稳定器的前部上安装有细长的整体式鼻部元件（20），其形成侧向导气表面以及鼻部的前端 （20）连接有穿孔金属板鼻状构件（25），并且其中鼻状件（20）的前端封闭并且在该封闭前端和鼻状构件（25）之间形成细长的空气通道（9） 形成了。
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6.发明公开Method for manufacturing a shell element reinforced with support elements 审中-公开Verfahren zur Herstellung eines mitStützelementenverstärktenMantelelements
公开(公告)号：EP2889123A1
公开(公告)日：2015-07-01
申请号：EP14193499.2
申请日：2014-11-17
发明人： Räckers, Bernd , Gerber, Martin
IPC分类号： B29C65/50
摘要： Method for manufacturing a shell element (5) reinforced with support elements (1, 3), having the following steps of:
(a) providing a skin element (7), which has an outer surface (9) and an inner surface (11) opposite the outer surface (9),
(b) providing a first support element (1), which has an attaching side (15) and a free side (17) is opposite the attaching side (15),
(c) attaching the first support element (1) on the skin element (7) such that the attaching side (15) of the first support element (1) faces the inner surface (11) of the skin element (7),
(d) introducing a first recess (25) into the first support element (1), which proceeds from the free side (17) of the first support element (1) and extends transversely to the first axis (13),
(e) providing a second support element (3), which has a support side (35) and a front side (37) opposite the support side (35),
(f) inserting the second support element (3) into the first recess (25) of the first support element (1) such that the support side (35) faces the inner surface (11) of the skin element (7), and
(g) attaching the second support element (3) on the first support element (1) and/or on the skin element (7).摘要翻译： 用于制造由支撑元件（1,3）加强的外壳元件（5）的方法，具有以下步骤：（a）提供具有外表面（9）和内表面（11）的表皮元件（7） ）与所述外表面（9）相对，（b）提供第一支撑元件（1），所述第一支撑元件（1）具有附接侧（15），并且自由侧（17）与所述附接侧（15）相对，（c） 第一支撑元件（1），使得第一支撑元件（1）的附接侧（15）面向皮肤元件（7）的内表面（11），（d）引入第一支撑元件 从第一支撑元件（1）的自由侧（17）延伸并且横向于第一轴线（13）延伸的第一支撑元件（1）的凹部（25），（e）提供第二支撑元件 3），其具有支撑侧（35）和与支撑侧（35）相对的前侧（37），（f）将第二支撑元件（3）插入第一支撑元件的第一凹部（25） 1） 其支撑面（35）面向皮肤元件（7）的内表面（11），并且（g）将第二支撑元件（3）附接在第一支撑元件（1）和/或皮肤元件（7）上 ）。
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7.发明授权Flow body, method for manufacturing a flow body and aircraft having such a flow body 有权流动体，制造流动体的方法和具有这种流动体的飞行器
公开(公告)号：EP2886452B1
公开(公告)日：2017-09-13
申请号：EP13198174.8
申请日：2013-12-18
发明人： Gerber, Martin
CPC分类号： B64C21/06 , B23K1/0008 , B23K1/20 , B29C65/76 , B64C5/02 , B64C5/06 , B64C2230/04 , B64C2230/22 , Y02T50/166 , Y10T29/49826
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8.发明公开Flow body, method for manufacturing a flow body and aircraft having such a flow body 审中-公开流动体及其制造方法的流体和飞机用这样的流动体
公开(公告)号：EP2891606A1
公开(公告)日：2015-07-08
申请号：EP14198674.5
申请日：2014-12-17
发明人： Gerber, Martin
摘要： An flow body (2) comprises a curved suction skin (16) having a first perforation, a leading edge (18) and two skin sections extending therefrom, wherein each skin section has an outer end (20, 22) facing away from the leading edge (18), an interior suction duct (42) having a second perforation (44) and extending through an inside of the curved suction skin (16) in a distance from the leading edge (18), and two sidewall members (54, 56), connected to the outer ends (20, 22), wherein the sidewall members (54, 56) are made of a composite material. The suction skin (16) comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin (16), wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin (16) to the local pressure maximum. The air sucking fuselage component requires less material and is easier to manufacture due to a smaller extension of a required suction area having the first perforation.
摘要翻译： 在流体（2）包括从所述主导背向弯曲吸入皮肤（16），具有第一穿孔，前缘（18）和两个表层部分延伸自那里，外端具有worin每个皮肤部分（20，22） 缘（18），具有第二穿孔（44）和从所述前缘（18）和两个侧壁部件中的距离，通过延伸到弯曲吸入皮肤（16）的内部的内部吸引用管道（42）（54， 56）连接到所述外端部（20，22），worin侧壁构件（54，56）由复合材料制成的。 吸入皮肤（16）包括成形轮廓形状，其在两个皮肤切片中的至少一个当空气在弯曲吸入皮肤（16），worin压力分布包括滞流点流动，一个吸力峰值bestimmt的压力分布 和随后的局部压力最大的吸力峰值的下游，worin第一穿孔从吸入皮肤（16）到所述本地最大压力上的滞流点延伸。 吸吮机身部件的空气需要较少的材料，并且由于具有第一穿孔所需的抽吸区域的较小的扩展部分更易于制造。
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9.发明公开Boundary layer control system and aircraft having such a boundary layer control system 审中-公开Grenzschichtsteuerung und Flugzeug mit dem Grenzschichtsteuersystem的系统
公开(公告)号：EP2886453A1
公开(公告)日：2015-06-24
申请号：EP13198176.3
申请日：2013-12-18
发明人： Gerber, Martin
IPC分类号： B64C21/06
CPC分类号： B64C21/06 , B64C2230/22 , Y02T50/166
摘要： A boundary layer control system in an aircraft comprises a outflow opening (20) arranged in a skin section (18) of the aircraft, which outflow opening (20) provides a suction force when air flows along the skin section (18), at least one duct couplable (14, 16) with the outflow opening (20) and coupled to an boundary layer control component (10) and an air control device (22). The air control device (22) is adapted for selectively providing air from a pressurized air source to the at least one duct (14, 16) for purging a perforation of the boundary layer control component (10) or inducing the suction of air through the boundary layer control component (10) to the outflow opening (20). Especially, bleed air from an APU in a tail region of the aircraft may be used for purging the boundary layer control component (10).
摘要翻译： 飞行器中的边界层控制系统包括布置在飞行器的皮肤部分（18）中的流出开口（20），该流出开口（20）至少在空气沿皮肤部分（18）流动时提供吸力 一个具有流出开口（20）并与边界层控制部件（10）和空气控制装置（22）连接的管道可连接（14,16）。 空气控制装置（22）适于选择性地将空气从加压空气源提供到至少一个管道（14,16），用于吹扫边界层控制部件（10）的穿孔或引起空气通过 边界层控制部件（10）到流出开口（20）。 特别地，可以使用来自飞行器尾部区域中的APU的排气来净化边界层控制部件（10）。
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10.发明公开Flow body, method for manufacturing a flow body and aircraft having such a flow body 有权流动体及其制造方法的流体和飞机用这样的流动体
公开(公告)号：EP2886452A1
公开(公告)日：2015-06-24
申请号：EP13198174.8
申请日：2013-12-18
发明人： Gerber, Martin
CPC分类号： B64C21/06 , B23K1/0008 , B23K1/20 , B29C65/76 , B64C5/02 , B64C5/06 , B64C2230/04 , B64C2230/22 , Y02T50/166 , Y10T29/49826
摘要： An flow body (2) comprises a curved suction skin (16) having a first perforation, a leading edge (18) and two skin sections extending therefrom, wherein each skin section has an outer end (20, 22) facing away from the leading edge (18), an interior suction duct (42) having a second perforation (44) and extending through an inside of the curved suction skin (16) in a distance from the leading edge (18), and two sidewall members (54, 56), connected to the outer ends (20, 22), wherein the sidewall members (54, 56) are made of a composite material. The suction skin (16) comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin (16), wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin (16) to the local pressure maximum. The air sucking fuselage component requires less material and is easier to manufacture due to a smaller extension of a required suction area having the first perforation.
摘要翻译： 在流体（2）包括从所述主导背向弯曲吸入皮肤（16），具有第一穿孔，前缘（18）和两个表层部分延伸自那里，外端具有worin每个皮肤部分（20，22） 缘（18），具有第二穿孔（44）和从所述前缘（18）和两个侧壁部件中的距离，通过延伸到弯曲吸入皮肤（16）的内部的内部吸引用管道（42）（54， 56）连接到所述外端部（20，22），worin侧壁构件（54，56）由复合材料制成的。 吸入皮肤（16）包括成形轮廓形状，其在两个皮肤切片中的至少一个当空气在弯曲吸入皮肤（16），worin压力分布包括滞流点流动，一个吸力峰值bestimmt的压力分布 和随后的局部压力最大的吸力峰值的下游，worin第一穿孔从吸入皮肤（16）到所述本地最大压力上的滞流点延伸。 吸吮机身部件的空气需要较少的材料，并且由于具有第一穿孔所需的抽吸区域的较小的扩展部分更易于制造。
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