公开(公告)号：WO2020130890A1

公开(公告)日：2020-06-25

申请号：PCT/SE2018/051325

申请日：2018-12-17

Applicant: SAAB AB

Inventor： RYDBOM, Anders ,  RING, Jakob ,  BARRKLEV, Mattias ,  PETERSSON, Mikael ,  DAVID, Edward

IPC: B29C33/50 ,  B29C33/44 ,  B29C70/28

Abstract: The present invention concerns a mould body assembly (1) and a method of forming a hollow feature (3) of an article (5), which hollow feature (3) is to be formed by the mould body assembly (1) extending along an imaginary axis (X). The mould body assembly (1) comprises a flexible caul member (7) and a rigid support member (9). The flexible caul member (7) is configured to be arranged onto the rigid support member (9) for bringing about a hollow feature forming surface (11) of the flexible caul member (7)configured to form the hollow feature (3). The flexible caul member (7) exhibits varying thickness for forming the hollow feature with trapping geometry.

公开(公告)号：WO2014116151A1

公开(公告)日：2014-07-31

申请号：PCT/SE2013/050053

申请日：2013-01-24

Applicant: SAAB AB

Inventor： LARSSON, Anders ,  PETERSSON, Mikael ,  LUNDBERG, Anders ,  NYMAN, Tonny ,  HALLSTRÖM, Stefan

IPC: B64C1/12 ,  B29C70/68 ,  B32B5/26 ,  B32B3/18 ,  B32B15/08 ,  B32B27/04

CPC classification number: B64C1/12 ,  B29C70/86 ,  B32B3/18 ,  B32B3/266 ,  B32B3/30 ,  B32B7/08 ,  B32B7/12 ,  B32B15/08 ,  B32B15/18 ,  B32B27/18 ,  B32B27/20 ,  B32B2260/023 ,  B32B2260/046 ,  B32B2307/54 ,  B32B2605/18 ,  Y02T50/43

Abstract: The present invention regards a composite laminate skin comprising a plurality of fiber reinforced plastic plies (7) stacked onto each other, the laminate skin (3) comprises a plurality of fastening apertures (9), each of which extending entirely or partly through the laminate skin (3) in a direction essentially orthogonally or orthogonally to the plane (P) of the laminate skin (3), each fastening aperture (9) being adapted for encompassing a respective fastening element (11). The fastening aperture (9) extends through a tailored stack (14) of at least two inserts (13) for taking up clamp forces in edge areas surrounding the fastening apertures so that the laminate skin can be made thinner. The invention also regards a method for manufacture of the laminate skin.

Abstract translation: 本发明涉及一种复合层压板，其包括彼此堆叠的多个纤维增强塑料层（7），层压表皮（3）包括多个紧固孔（9），每个紧固孔（9）完全或部分地穿过层压板 皮肤（3）在基本上与层压体皮肤（3）的平面（P）正交或正交的方向上，每个紧固孔（9）适于包围相应的紧固元件（11）。 紧固孔（9）延伸穿过至少两个插入件（13）的定制叠层（14），用于在围绕紧固孔的边缘区域中卷取夹紧力，使得层压体皮肤可以变薄。 本发明还涉及一种制造层压体皮肤的方法。

公开(公告)号：WO2010050860A1

公开(公告)日：2010-05-06

申请号：PCT/SE2008/051225

申请日：2008-10-29

Applicant: SAAB AB ,  HALLANDER, Per ,  PETERSSON, Mikael

Inventor： HALLANDER, Per ,  PETERSSON, Mikael

IPC: B29C70/44 ,  B29C43/12 ,  B29C51/10 ,  B29C51/36

CPC classification number: B29C70/44

Abstract: The invention relates to an apparatus and a method of conforming a blank (15) onto forming surface sections (5) of a forming tool (7) by drawing a first vacuum against an elastic forming medium (1) for transmitting forming forces from the elastic forming medium (1) to the blank (15), the method includes the steps of evacuating the elastic forming medium (1) with the first vacuum for allowing the elastic forming medium (1) to stretch and conform the blank (15) to the forming surface sections (5). The elastic forming medium (1) comprises at least one void (3), and a step of applying a second vacuum to the void (3) is performed for achieving a stiffened section (4) of the elastic forming medium (1) corresponding with the location of the void (3) and corresponding with, when the elastic forming medium (1) after the completion lies against the forming tool (7) having the blank (15) in between, a forming surface section (5) of the forming tool (7) where the blank (15) requires a forming force (F) being larger than that of surrounding sections (17) of the elastic forming medium (1).

Abstract translation: 本发明涉及一种将坯料（15）与成形工具（7）的成形表面部分（5）相吻合的装置和方法，该方法是通过将弹性成形介质（1）拉伸第一真空，以从弹性体 在坯料（15）上形成介质（1）的方法包括以下步骤：用第一真空抽吸弹性成形介质（1），使弹性成形介质（1）拉伸并使坯件（15）与 形成表面部分（5）。 弹性成形介质（1）包括至少一个空隙（3），并且执行向空隙（3）施加第二真空的步骤，以实现对应于弹性成形介质（1）的加强部分（4） 当完成后的弹性成形介质（1）抵靠在其间具有坯料（15）的成形工具（7）时，空隙（3）的位置和对应的形成工序 工具（7），其中坯料（15）需要大于弹性成形介质（1）的周围部分（17）的成形力（F）。

公开(公告)号：WO2021167504A1

公开(公告)日：2021-08-26

申请号：PCT/SE2020/050183

申请日：2020-02-17

Applicant: SAAB AB

Inventor： PETERSSON, Mikael ,  STRANDBERG, Adam

IPC: B64C1/06 ,  B29C65/70 ,  B29C70/34 ,  B29C70/38 ,  B64C3/18 ,  B29D99/00

Abstract: The present invention regards a profile manufacturing tool assembly (1003) configured for manufacture of a curved aerospace profile article (101) and a method of manufacture of a curved aerospace profile article (101) made of fibre reinforced matrix material. A profile manufacturing tool assembly (1003) comprises a first tool device (1005) configured to form a curved openbeam profile workpiece (19); a second tool device (1022) configured to divide in longitudinal direction the curved openbeam profile workpiece (19) in at least a first and second profile (33, 35); a third tool device (1049) configured to join the first and second profile (33, 35) to each other for providing said curved aerospace profile article (101); a fourth tool device (1061) configured to cure the curved openbeam profile workpiece (19) or configured to cure the first and second profile (33, 35) prior said joining or after said joining and removing after the curing step the curved aerospace profile article (101) from the fourth tool device (1061).

公开(公告)号：WO2015094059A1

公开(公告)日：2015-06-25

申请号：PCT/SE2013/051586

申请日：2013-12-20

Applicant: SAAB AB

Inventor： HALLANDER, Per ,  LUNDBERG, Anders ,  NYMAN, Tonny ,  PETERSSON, Mikael

IPC: B64C1/12 ,  B29C43/02 ,  B29C65/70 ,  B29C70/50 ,  B29C70/68 ,  B29D99/00

CPC classification number: B29C65/48 ,  B29C65/02 ,  B29C66/00145 ,  B29C70/382 ,  B29C70/386 ,  B29D99/0014 ,  B29K2105/06 ,  B29L2031/3076 ,  B64C1/061 ,  B64C1/064 ,  B64C1/12 ,  Y02T50/43

Abstract: A stiffening element 11 comprising at least a first stiffening profile 1and at least a second stiffening profile 2. The first stiffening profile 1 comprises a profile member 4, at least one structural flange 8 is connected to the profile member 4, a through-passage 9 extending through the profile member 4,and at least one support flange 10 is connected to the profile member 4.The second stiffening profile 2 comprises a bottom portion 12 and at least one support side portion 13 connected to the bottom portion 12. Furthermore, the invention relates to a method for manufacturing a stiffening element 11 and a method for manufacturing a reinforced structure 15, wherein the reinforced structure 15 comprises at least one structural element 14 and at least one stiffening element 11.

Abstract translation: 包括至少第一加强轮廓1和至少第二加强轮廓2的加强元件11.第一加强轮廓1包括轮廓构件4，至少一个结构凸缘8连接到轮廓构件4，通道9 延伸穿过轮廓构件4，并且至少一个支撑凸缘10连接到轮廓构件4.第二加强轮廓2包括底部12和连接到底部12的至少一个支撑侧部13。 本发明涉及一种用于制造加强元件11的方法和用于制造加强结构15的方法，其中加强结构15包括至少一个结构元件14和至少一个加强元件11。

公开(公告)号：WO2013089598A1

公开(公告)日：2013-06-20

申请号：PCT/SE2011/051501

申请日：2011-12-12

Applicant: SAAB AB ,  GRANKÄLL, Tommy ,  HALLANDER, Per ,  PETERSSON, Mikael ,  WEIDMANN, Björn

Inventor： GRANKÄLL, Tommy ,  HALLANDER, Per ,  PETERSSON, Mikael ,  WEIDMANN, Björn

IPC: B64C3/20 ,  B29C65/02 ,  B29C65/48 ,  B29C70/54 ,  B64C1/12 ,  B64C3/24 ,  B29L31/30

CPC classification number: B64C1/00 ,  B29C65/4835 ,  B29C65/488 ,  B29C65/54 ,  B29C66/112 ,  B29C66/1122 ,  B29C66/131 ,  B29C66/545 ,  B29C66/63 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/7311 ,  B29C66/73752 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/81455 ,  B29C66/9141 ,  B29C66/91441 ,  B29C66/91921 ,  B29D99/0028 ,  B29L2031/3085 ,  B64C3/187 ,  B64C3/20 ,  B64C3/24 ,  Y02T50/43 ,  Y10T428/24521 ,  B29K2307/04 ,  B29K2309/08

Abstract: The present invention regards an aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) by means of a bonding material (15). It also regards a method of manufacture of the aircraft structure. The bonding material (15) comprises a non-structural fiber reinforced resin system, wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15), due to settlement of resin of the non-structural fiber reinforced resin system in said interior face filling volume (21) during the viscous phase of the curing of the non-structural fiber reinforced resin system.

Abstract translation: 本发明涉及一种包括空气动力学复合材料壳体（7）的飞机结构，其内表面（9）全部或部分地通过至少一个二维或三维结构复合材料部件（11）与 接合材料（15）。 它还涉及飞机结构的制造方法。 接合材料（15）包括非结构纤维增强树脂体系，其中在空间上对应于内表面填充体积（21）的部分的粘合材料的至少一部分比粘结材料的其它部分 15），由于在非结构纤维增强树脂体系的固化粘性相中，所述内表面填充体积（21）中的非结构纤维增强树脂体系的树脂沉降。

公开(公告)号：WO2012099512A1

公开(公告)日：2012-07-26

申请号：PCT/SE2011/050063

申请日：2011-01-21

Applicant: SAAB AB ,  GRANKÄLL, Tommy ,  HALLANDER, Per ,  LUNDBERG, Anders ,  NYMAN, Tonny ,  WEIDMANN, Björn ,  PETERSSON, Mikael

Inventor： GRANKÄLL, Tommy ,  HALLANDER, Per ,  LUNDBERG, Anders ,  NYMAN, Tonny ,  WEIDMANN, Björn ,  PETERSSON, Mikael

IPC: B29C70/20 ,  B29C70/34 ,  B29C70/88 ,  B32B5/26

CPC classification number: B32B5/26 ,  B29C70/222 ,  B29C70/30 ,  B29C70/342 ,  B29C70/46 ,  B32B2250/05 ,  B32B2250/20 ,  B32B2260/023 ,  Y10T428/24124

Abstract: The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 80 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most of or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 and the stack further comprises a plurality of plies having fibres substantially in the same direction 811 as the longitudinally direction L of the article 801 and / or a plurality of plies having fibres in the diagonal direction (812, 813, 815, 816, 817, 818) of the longitudinal direction (L) of the article (801), wherein at least one of the ply / plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 comprise fibres that are stiffer than the fibres in the other plies which have less stiff fibres. The present invention also relates to a method of forming an article on a tool, the tool having one longitudinal direction L and one transversal direction T.

Abstract translation: 本发明涉及一种复合制品801，其中制品具有纵向方向L和横向方向T，制品80包括一叠层，其中一层是底层，一层是顶层，大部分或 所有帘布层都包括纤维，并且制品包括多个帘布层，其具有基本上在与制品801的纵向方向L相关的正交方向810上的纤维，并且该堆叠还包括多个帘布层，其具有基本上沿相同方向811的纤维 物品801的纵向方向L和/或具有在物品（801）的纵向方向（L）上的对角方向（812,813,815,816,817,818）的纤维的多个帘布层，其中在 具有基本上在与制品801的纵向方向L相关的正交方向810上的纤维的帘布层/帘布层中的至少一个包括比其他帘布层中具有较低刚度的纤维更硬的纤维 纤维。 本发明还涉及一种在工具上形成物品的方法，该工具具有一个纵向方向L和一个横向方向T.

公开(公告)号：WO2010062234A1

公开(公告)日：2010-06-03

申请号：PCT/SE2008/051374

申请日：2008-11-28

Applicant: SAAB AB ,  WESTERDAHL, Anders ,  HALLANDER, Per ,  ANDERSSON, Jan ,  PETERSSON, Mikael

Inventor： WESTERDAHL, Anders ,  HALLANDER, Per ,  ANDERSSON, Jan ,  PETERSSON, Mikael

IPC: B29C51/42 ,  B29C51/18 ,  B29C70/00

CPC classification number: B29C51/28 ,  B29C51/424

Abstract: The invention regards a thermoforming apparatus for forming a blank (3) into a composite article, the thermoforming apparatus (1) comprises a forming tool (5), a forming member (7 ) for forming the blank (3) over the forming tool (5), the forming member (7) separates a first chamber (11),arranged for containing the blank (3), from a second chamber (13). The first chamber(11)comprises a first air circulation means (2, 21) for circulating air (a) in said first chamber (11) for achieving a heat distribution to the blank (3). It also regards a method for forming the blank (3) during the circulation of air (a) in said first chamber (11).

Abstract translation: 本发明涉及一种用于将坯料（3）形成复合制品的热成型设备，该热成型设备（1）包括成形工具（5），用于在成形工具上形成坯件（3）的成形构件（7） 如图5所示，形成构件（7）从第二室（13）分离用于容纳坯料（3）的第一室（11）。 第一室（11）包括用于使所述第一室（11）中的空气（a）循环以实现对坯料（3）的热分配的第一空气循环装置（2,21）。 还涉及在空气（a）在所述第一室（11）的循环期间形成坯料（3）的方法。

公开(公告)号：WO2007104674A1

公开(公告)日：2007-09-20

申请号：PCT/EP2007/052090

申请日：2007-03-06

Applicant: SAAB AB ,  PETERSSON, Mikael

Inventor： PETERSSON, Mikael

IPC: H01Q15/14 ,  B29C70/00

CPC classification number: H01Q15/144 ,  B29C70/78 ,  B29C70/865 ,  Y10S343/02

Abstract: The present invention refers to a reflector comprising a reflector dish 2 and a backing structure 5, wherein the reflector dish 2 has a reflecting surface 3 and a back surface 4, and wherein the backing structure 5 is arranged in a pattern on the back surface 4 of the reflector dish 2 for supporting and stiffening the reflector dish 2, wherein the backing structure 5 comprises a first backing structure skin 6 and a second backing structure skin 7 and a backing structure core 8 there between, wherein the core 8 is substantially thicker than each skin 6, 7 and the backing structure 5 is arranged such that the first backing structure skin 6 is faced against the back surface 4 of the reflector dish 2. The present invention also refers to a method of manufacturing a reflector.

Abstract translation: 本发明涉及一种包括反射器皿2和背衬结构5的反射器，其中反射器皿2具有反射表面3和背面4，并且其中背衬结构5以图案布置在背面4上 用于支撑和加强反射器皿2的反射器皿2，其中背衬结构5包括第一背衬结构皮肤6和第二背衬结构皮肤7和其间的背衬结构芯部8，其中芯部8基本上比 每个皮肤6,7和背衬结构5被布置成使得第一背衬结构皮肤6面向反射器皿2的后表面4.本发明还涉及制造反射器的方法。

公开(公告)号：WO2014200393A1

公开(公告)日：2014-12-18

申请号：PCT/SE2013/050655

申请日：2013-06-10

Applicant: SAAB AB

Inventor： LINDBÄCK, Jan-Erik ,  PETERSSON, Mikael ,  WAARA, Jan ,  JOHANSSON, Peter

IPC: B64C1/12 ,  B29C70/30 ,  B64C1/06 ,  B64C3/18 ,  B64C3/20 ,  B64C3/26

CPC classification number: B64C1/12 ,  B29C70/342 ,  B29C70/44 ,  B29C70/545 ,  B29C2793/0027 ,  B29C2793/0063 ,  B29C2793/0081 ,  B29D99/0014 ,  B29L2031/085 ,  B29L2031/3076 ,  B64C1/064 ,  B64C2001/0072 ,  F03D1/0675 ,  Y02E10/721 ,  Y02P70/523 ,  Y02T50/43

Abstract: The present invention relates to a method and apparatus for manufacture of stringer reinforced composite skins. The method includes the consecutive steps of: providing a forming tool comprising elongated support members spaced apart by means of elongated dummy members. The support and dummy members may be assembled side by side longitudinally such that the long sides of the support and dummy members are essentially parallelly aligned. In a first fibre placement step fibre reinforced resin is placed onto said forming tool, to form a fibre reinforced skin on said forming tool. The fibre reinforced skin is cut along the longitudinal extension of the dummy members so as to cut out fibre reinforced blank materials for stringer members. The dummy members are removed. The fibre reinforced blank materials are formed so that the fibre reinforced blank materials are shaped around said support members to form stringer members. The stringer members are assembled by longitudinally bringing together the stringer members so that the long sides of the stringer members are essentially parallelly aligned, to form a stringer unit. In a second fibre placement step fibre reinforced resin is placed onto said stringer unit, to form a fibre reinforced skin onto said stringer unit. The fibre reinforced skin and said stringer unit are co-cured to form a stringer reinforced composite skin. The support members are then removed from said stringer reinforced composite skin.

Abstract translation: 本发明涉及一种用于制造纵梁加强复合材料表皮的方法和装置。 该方法包括以下连续步骤：提供一种成形工具，该成形工具包括通过细长的虚拟构件间隔开的细长的支撑构件。 支撑件和虚拟构件可以纵向并排组装，使得支撑件和虚拟构件的长边基本上平行对准。 在第一纤维放置步骤中，将纤维增强树脂放置在所述成形工具上，以在所述成形工具上形成纤维增强皮肤。 沿着虚拟构件的纵向延伸部分切割纤维增强的皮肤，以切割用于桁条构件的纤维增强的坯料。 虚拟构件被移除。 纤维增强的坯料形成为使得纤维增强的坯料围绕所述支撑构件成形以形成纵梁构件。 纵梁构件通过纵向收合纵梁构件而组装，使得纵梁构件的长边基本上平行对齐，以形成纵梁单元。 在第二纤维放置步骤中，将纤维增强树脂放置在所述纵梁单元上，以在所述纵梁单元上形成纤维增强皮肤。 纤维增强皮肤和所述纵梁单元被共同固化以形成纵梁增强复合皮肤。 然后将支撑构件从所述纵梁增强复合材料表皮中取出。