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1. 发明授权

US09150941B2 Method for preventing crack formation and for slowing down the advancement of a crack in metal aircraft structures by means of laser shock rays 有权
标题翻译：通过激光冲击射线防止裂纹形成和减缓金属飞机结构中的裂纹进展的方法
公开(公告)号：US09150941B2
公开(公告)日：2015-10-06
申请号：US13111405
申请日：2011-05-19
申请人： Juergen Steinwandel , Domenico Furfari , Nikolaus Ohrloff , Claudio Dalle Donne
发明人： Juergen Steinwandel , Domenico Furfari , Nikolaus Ohrloff , Claudio Dalle Donne
IPC分类号： B23K26/00 , C21D10/00 , B64F5/00
CPC分类号： C21D10/005 , B64F5/40 , C21D10/00
摘要： The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.
摘要翻译：本发明提供一种通过激光冲击硬化来防止形成裂纹并减缓金属飞机结构部件中的裂纹扩展的方法，具有以下步骤：提供具有裂纹的飞机结构部件; 用具有第一波长和第一脉动频率的第一脉冲激光束照射靠近裂纹的飞机结构部分的第一表面区域，其中第一激光束的能量被飞机结构部件吸收，冲击波穿过飞机结构部分，在飞机结构部分产生压缩预应力。

2. 发明授权

US08998065B2 Method and device for the friction stir welding of two components 有权
标题翻译：用于摩擦搅拌焊接的两个部件的方法和装置
公开(公告)号：US08998065B2
公开(公告)日：2015-04-07
申请号：US13077117
申请日：2011-03-31
申请人： Domenico Furfari , Marco Pacchione
发明人： Domenico Furfari , Marco Pacchione
IPC分类号： B23K20/12 , B23K31/02 , B23K37/08
CPC分类号： B23K20/129 , B23K20/002 , B23K20/122 , B23K20/123 , B23K20/124 , B23K20/1245 , B23K20/126 , B23K20/1275 , B23K20/26 , B23K31/02 , B23K37/08
摘要： A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.
摘要翻译：一种用于飞行器和航天器的机身结构的两个部件，特别是两个壳体部件的摩擦搅拌焊接的方法，所述方法包括以下方法步骤：将两个部件相对于彼此定位成使得连接两部分之间形成区域; 通过摩擦搅拌焊接工具摩擦搅拌焊接两个部件，该工具穿透连接区域，以便产生在形成连接区域的未穿透焊接边缘部分的连接区域上的焊缝; 并至少在连接区域的焊接边缘部分引入内部压缩应力。此外，还提供了一种用于飞行器和航天器的机身结构的两个部件，特别是两个壳部件的摩擦搅拌焊接的装置。

3. 发明申请

US20110248070A1 METHOD AND DEVICE FOR THE FRICTION STIR WELDING OF TWO COMPONENTS 有权
标题翻译：用于两个部件的摩擦焊接的方法和装置
公开(公告)号：US20110248070A1
公开(公告)日：2011-10-13
申请号：US13077117
申请日：2011-03-31
申请人： Domenico Furfari , Marco Pacchione
发明人： Domenico Furfari , Marco Pacchione
IPC分类号： B23K20/12
CPC分类号： B23K20/129 , B23K20/002 , B23K20/122 , B23K20/123 , B23K20/124 , B23K20/1245 , B23K20/126 , B23K20/1275 , B23K20/26 , B23K31/02 , B23K37/08
摘要： A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.
摘要翻译：一种用于飞行器和航天器的机身结构的两个部件，特别是两个壳体部件的摩擦搅拌焊接的方法，所述方法包括以下方法步骤：将两个部件相对于彼此定位，使得连接两部分之间形成区域; 通过摩擦搅拌焊接工具摩擦搅拌焊接两个部件，该工具穿透连接区域，以便产生在形成连接区域的未穿透焊接边缘部分的连接区域上的焊缝; 并至少在连接区域的焊接边缘部分引入内部压缩应力。此外，还提供了一种用于飞行器和航天器的机身结构的两个部件，特别是两个壳部件的摩擦搅拌焊接的装置。

4. 发明申请

US20130149501A1 METHOD FOR CONNECTING A FIBRE COMPOSITE COMPONENT TO A STRUCTURAL COMPONENT OF AN AIRCRAFT AND SPACECRAFT AND A CORRESPONDING ARRANGEMENT 审中-公开
标题翻译：将光纤复合部件连接到飞机和机架的结构部件的方法以及相应的布置
公开(公告)号：US20130149501A1
公开(公告)日：2013-06-13
申请号：US13486444
申请日：2012-06-01
申请人： Marco PACCHIONE , Domenico FURFARI
发明人： Marco PACCHIONE , Domenico FURFARI
IPC分类号： B32B7/08 , B23P13/00
CPC分类号： B32B7/08 , B23P13/00 , B29C35/02 , B29C65/344 , B29C65/3444 , B29C65/3448 , B29C65/3476 , B29C65/364 , B29C65/3644 , B29C65/3656 , B29C65/368 , B29C65/483 , B29C65/5021 , B29C65/5057 , B29C65/564 , B29C66/1122 , B29C66/30341 , B29C66/43 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72143 , B29C66/73751 , B29C66/73752 , B29C66/73753 , B29C66/73754 , B29C66/73921 , B29C66/742 , B29K2101/12 , B29K2105/06 , B29K2105/24 , B29K2105/243 , B29K2105/246 , B29K2305/00 , B29K2307/00 , B29L2031/3076 , B64C2001/0072 , F16B15/0023 , F16B15/0046 , Y02T50/43 , Y10T29/49622 , Y10T428/24612 , B29K2307/04
摘要： In the case of a method for connecting a fibre composite component to a structural component of an aircraft and spacecraft, a metal foil is provided as a transverse reinforcement element between the fibre composite component and the structural component. It is formed with at least one anchoring portion which protrudes from the surface facing the fibre composite component and is inserted between the fibre composite component and the structural component. A corresponding arrangement is produced in accordance with this method.
摘要翻译：在将纤维复合材料部件连接到飞行器和航天器的结构部件的方法的情况下，在纤维复合部件和结构部件之间设置金属箔作为横向加强元件。形成有至少一个从面向纤维复合部件的表面突出的锚固部分，并且插入到纤维复合部件和结构部件之间。根据该方法制作相应的布置。

5. 发明申请

US20110290770A1 METHOD FOR PREVENTING CRACK FORMATION AND FOR SLOWING DOWN THE ADVANCEMENT OF A CRACK IN METAL AIRCRAFT STRUCTURES BY MEANS OF LASER SHOCK RAYS 有权
标题翻译：用于防止裂纹形成并缓慢降低金属飞机结构裂纹的方法，采用激光击球方法
公开(公告)号：US20110290770A1
公开(公告)日：2011-12-01
申请号：US13111405
申请日：2011-05-19
申请人： Juergen Steinwandel , Domenico Furfari , Nikolaus Ohrloff , Claudio Dalle Donne
发明人： Juergen Steinwandel , Domenico Furfari , Nikolaus Ohrloff , Claudio Dalle Donne
IPC分类号： B23K26/00
CPC分类号： C21D10/005 , B64F5/40 , C21D10/00
摘要： The present invention provides a method for preventing the forming of cracks and slowing the crack propagation in metallic airplane structural parts by laser shock peening with the following steps: Providing an airplane structural part having a crack; irradiating a first surface area of the airplane structural part close to the crack with a first pulsed laser beam having a first wavelength and a first pulsation frequency, wherein energy of the first laser beam is absorbed by the airplane structural part and a shock wave runs through the airplane structural part, which creates compressive prestressings in the airplane structural part.
摘要翻译：本发明提供一种通过激光冲击硬化来防止形成裂纹并减缓金属飞机结构部件中的裂纹扩展的方法，具有以下步骤：提供具有裂纹的飞机结构部件; 用具有第一波长和第一脉动频率的第一脉冲激光束照射靠近裂纹的飞机结构部分的第一表面区域，其中第一激光束的能量被飞机结构部件吸收，冲击波穿过飞机结构部分，在飞机结构部分产生压缩预应力。

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