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1. 发明申请

WO2011096861A1 A SMOOTH SURFACE FORMING TOOL AND MANUFACTURE THEREOF 审中-公开
标题翻译：一个SMOOTH表面成型工具及其制造
公开(公告)号：WO2011096861A1
公开(公告)日：2011-08-11
申请号：PCT/SE2010/050136
申请日：2010-02-04
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
IPC分类号： B29C33/40 , B29C70/30 , B29C70/54 , B29C70/64 , B29C70/82
CPC分类号： B64F5/0009 , B29C33/40 , B29C45/73 , B29C70/443 , B29C70/88 , B29K2105/165 , B64F5/10 , B82Y30/00 , H05B2214/04 , Y10T156/10
摘要： The present invention regards an aircraft article composite forming tool (3) and a method for producing the tool (3), the aircraft article (2) to be formed comprises a composite material including an outer surface (9), the aircraft 5 article composite forming tool (3) comprises a matrix laminate (11) made of at least an upper ply (P1) including a forming surface (7) for forming said aircraft article (2) and outer surface (9). The upper ply (P1) comprises a nano filament structure (15) embedded 10 therein.
摘要翻译：本发明涉及飞机制品复合成形工具（3）和用于生产工具（3）的方法，待形成的飞机制品（2）包括复合材料，其包括外表面（9），飞机5物品复合材料成形工具（3）包括由包括用于形成所述飞机制品（2）和外表面（9）的成形表面（7）的至少上层（P1）制成的基质层压体（11）。上层（P1）包括嵌入10的纳米长丝结构（15）。

2. 发明申请

WO2010144007A1 NANO-REINFORCED RADIUS FILLER FOR AN AIRCRAFT STRUCTURE AND A METHOD OF PRODUCING AN AIRCRAFT STRUCTURE COMPRISING SUCH FILLER 审中-公开
标题翻译：用于飞机结构的纳米增强半径填料和一种生产包含这种填料的飞机结构的方法
公开(公告)号：WO2010144007A1
公开(公告)日：2010-12-16
申请号：PCT/SE2009/050716
申请日：2009-06-11
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
IPC分类号： B29C70/14 , B29C65/00 , B64C1/06
CPC分类号： B64C1/06 , B29C35/02 , B29C65/02 , B29C66/112 , B29C66/1122 , B29C66/131 , B29C66/43441 , B29C66/49 , B29C66/496 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73754 , B29C66/73941 , B29C70/14 , B29C70/46 , B29K2105/06 , B29K2105/167 , B29K2105/243 , B29K2307/00 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , Y02T50/43 , Y10T428/24479 , B29K2307/04 , B29K2071/00 , B29K2067/00 , B29K2063/00 , B29K2031/00 , B29K2049/00 , B29K2061/04 , B29K2079/08 , B29K2081/04
摘要： The present invention relates to a composite radius filler for use in an aircraft structure (2), which comprises structural composite parts (7) assembled together to form the aircraft structure (2). The composite radius filler (3) is arranged between rounded sections (5', 5") of the structural composite parts (7) for filling a gap (4) formed between the structural composite parts (7). The composite radius filler (3) is made structural by a nanostructure (23) arranged within the composite radius filler (3) for the reinforcement of the interface between the radius filler (3) and the structural composite part (7). The invention also relates to a method for producing an aircraft structure comprising said nano-reinforced radius filler.
摘要翻译：本发明涉及一种用于飞机结构（2）的复合半径填料，其包括组装在一起以形成飞行器结构（2）的结构复合部件（7）。复合半径填料（3）设置在结构复合部件（7）的圆形部分（5'，5“）之间，用于填充形成在结构复合部件（7）之间的间隙（4），复合半径填料）由布置在复合半径填料（3）内的纳米结构（23）构成，用于加强半径填料（3）和结构复合材料部件（7）之间的界面，本发明还涉及一种生产包括所述纳米增强半径填料的飞机结构。

3. 发明申请

WO2011142699A1 A COMPOSITE ARTICLE COMPRISING PARTICLES AND A METHOD OF FORMING A COMPOSITE ARTICLE 审中-公开
标题翻译：包含颗粒的复合材料和形成复合材料的方法
公开(公告)号：WO2011142699A1
公开(公告)日：2011-11-17
申请号：PCT/SE2010/050518
申请日：2010-05-11
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , NORDIN, Pontus
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , NORDIN, Pontus
IPC分类号： B29C70/22 , B29C70/34 , B29C70/54
CPC分类号： B32B5/12 , B29C70/025 , B29C70/202 , B29C70/342 , B29K2105/243 , Y02T50/43 , Y10T428/24124
摘要： The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 801 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 and substantially in the same direction 811 as the longitudinally direction L of the article 801, wherein the bottom ply and the top ply have fibres in a substantially orthogonal direction 810 to the longitudinal L direction of the article 801, at least one ply has the fibres substantially in the same direction 811 as the longitudinal direction L of the article 801, wherein at least one of the ply/plies having fibres substantially in the longitudinal direction L comprise/s particles selected from the group of thermoplastic tougheners, nano particles, micro particles, elastic particles, elastomer particles and polymer particles or a combination of them. The present invention also relates to an method of forming an article on a tool.
摘要翻译：本发明涉及复合制品801，其中制品具有纵向方向L和横向方向T，制品801包括一叠层，其中一层是底层，一层是顶层，大部分或全部帘布层包括纤维，并且制品包括多个帘布层，其具有基本上在正交方向810上的纤维并且基本上沿与制品801的纵向方向L相同的方向811，其中底层和顶层具有纤维与物品801的纵向L方向基本上正交的方向810，至少一个帘布层具有与制品801的纵向方向L基本上沿相同方向811的纤维，其中至少一个具有纤维的帘布层/ 在纵向方向L包括选自热塑性增韧剂，纳米颗粒，微粒，弹性颗粒，弹性体颗粒 es和聚合物颗粒或它们的组合。本发明还涉及在工具上形成制品的方法。

4. 发明申请

WO2011087413A1 ARTICLE WITH DE-ICING/ANTI-ICING FUNCTION 审中-公开
标题翻译：具有去除/反制功能的文章
公开(公告)号：WO2011087413A1
公开(公告)日：2011-07-21
申请号：PCT/SE2010/050029
申请日：2010-01-14
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
IPC分类号： B64D15/12 , H05B3/14
CPC分类号： H05B3/267 , B64D15/12 , B64D45/02 , H05B2214/02 , H05B2214/04
摘要： The present invention regards a structural article comprising an outer surface (5), which serves as an aerodynamic surface when the structural article (1) is subjected for an air stream, the structural article (1 ) comprises a resin matrix laminate (7) including an upper ply (P1 ) and a bottom ply (P3, P4, P6)$ a heating element (13) is arranged in contact with the bottom ply (P3, P4, P6) and coupled to a power supply unit (45) in purpose to de-ice/anti-ice the outer surface (5). Each ply (P1, P2.... P6) comprises a thermally conductive filament structure (9) having a filament orientation such that the prolongation of the filaments (11 ) has an extension essentially perpendicular to the extension of the laminate (7).
摘要翻译：本发明涉及一种包括外表面（5）的结构制品，该外表面（5）当结构制品（1）经受空气流时用作空气动力学表面，结构制品（1）包括树脂基质层压板（7），其包括加热元件（13）布置成与底层（P3，P4，P6）接触并连接到电源单元（45）的上层（P1）和底层（P3，P4，P6）目的是去冰/防冰外表面（5）。每个帘布层（P1，P2 ... P6）包括具有长丝取向的导热细丝结构（9），使得长丝（11）的延长部具有基本垂直于层压体（7）的延伸部的延伸部。

5. 发明申请

WO2010144010A1 A STRUCTURAL LONGITUDINAL COMPOSITE JOINT FOR AIRCRAFT STRUCTURE 审中-公开
标题翻译：用于飞机结构的结构纵向复合材料接头
公开(公告)号：WO2010144010A1
公开(公告)日：2010-12-16
申请号：PCT/SE2009/050719
申请日：2009-06-11
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , STRINDBERG, Göte , NORDIN, Pontus , ÖNNEFORS, Rustan , GRANKÄLL, Tommy
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , STRINDBERG, Göte , NORDIN, Pontus , ÖNNEFORS, Rustan , GRANKÄLL, Tommy
IPC分类号： B64C1/00 , B29C65/48 , B29C70/30 , B32B3/10 , B32B5/28 , B64C3/20 , B64C3/26 , B82B1/00 , B29C65/50 , B29C65/52
CPC分类号： B29C70/58 , B29C65/4875 , B29C65/488 , B29C65/5014 , B29C65/5021 , B29C65/5057 , B29C66/1142 , B29C66/43 , B29C66/435 , B29C66/721 , B29C70/30 , B29K2031/00 , B29K2063/00 , B29K2067/00 , B29K2071/00 , B29K2079/085 , B29K2081/04 , B29K2101/10 , B29K2101/12 , B29K2105/06 , B29K2105/167 , B29K2307/00 , B29K2309/02 , B29K2309/08 , B29L2031/3076 , B29L2031/3085 , B32B3/02 , B32B3/14 , B32B3/18 , B32B5/02 , B32B5/22 , B32B5/26 , B32B5/28 , B32B7/005 , B32B2250/20 , B32B2260/021 , B32B2260/046 , B32B2262/02 , B32B2262/101 , B32B2262/105 , B32B2262/106 , B32B2307/50 , B32B2307/558 , B32B2605/18 , B64C3/20 , B64C3/26 , Y02T50/43 , Y10T428/16 , Y10T428/17 , Y10T428/18 , B29C65/00
摘要： The present invention regards a structural composite part made of pre-impregnated fibre plies (5). The edges (7) of two adjacent fibre plies (5) are connected via a longitudinal composite joint (9) made structural by a nanostructure (41) arranged within the composite joint (9). The invention concerns also a method of producing a structural composite part (11) made of pre-impregnated fibre plies wherein the edges (7) of two adjacent fibre plies (5) are connected via a longitudinal composite joint (9) made structural by a nanostructure (41) and an aircraft structure, such as a wing, comprising such structural composite parts (11).
摘要翻译：本发明涉及由预浸纤维层（5）制成的结构复合部件。两个相邻的纤维层（5）的边缘（7）通过由布置在复合接头（9）内的纳米结构（41）构成的纵向复合接头（9）连接。本发明还涉及一种生产由预浸纤维层制成的结构复合部件（11）的方法，其中两个相邻纤维层（5）的边缘（7）经由纵向复合接头（9）连接，所述纵向复合接头（9）由纳米结构（41）和包括这种结构复合部件（11）的飞机结构，例如机翼。

6. 发明申请

WO2010144009A1 AN AIRCRAFT STRUCTURE WITH STRUCTURAL PARTS CONNECTED BY NANOSTRUCTURE AND A METHOD FOR MAKING SAID AIRCRAFT STRUCTURE 审中-公开
标题翻译：具有由纳米结构连接的结构部件的飞机结构和用于制造具有描述性的飞机结构的方法
公开(公告)号：WO2010144009A1
公开(公告)日：2010-12-16
申请号：PCT/SE2009/050718
申请日：2009-06-11
申请人： SAAB AB , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
发明人： HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn , GRANKÄLL, Tommy , STRINDBERG, Göte , NORDIN, Pontus
IPC分类号： B64C1/00 , B29C65/48 , B29C65/52 , B64C3/20 , B64C3/26 , B64C7/00 , B82B1/00
CPC分类号： B64C1/00 , B29C65/4875 , B29C65/488 , B29C65/5057 , B29C66/112 , B29C66/131 , B29C66/543 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72143 , B29C66/73711 , B29K2105/06 , B29K2105/167 , B29K2307/00 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B64C2001/0072 , B82Y30/00 , Y02T50/43 , Y10T428/24124 , Y10T428/24488 , Y10T428/249921 , Y10T428/31511 , B29K2307/04 , B29K2063/00
摘要： The present invention regards an aircraft structure comprising structural composite parts (5) assembled together to form said aircraft structure (3); said aircraft structure (3) further comprises a bonding interlayer material provided (17) to bond said structural composite parts (5) to each other. The bonding interlayer material (17) comprises a nanostructure enhanced material (20, 21). The invention also regards a method of producing an aircraft structure of assembled structural composite parts (5), being cured or semi-cured before said assembly.
摘要翻译：本发明涉及一种飞机结构，其包括组装在一起以形成所述飞行器结构（3）的结构复合部件（5）。所述飞行器结构（3）还包括用于将所述结构复合部件（5）彼此粘合的接合中间层材料（17）。粘合中间层材料（17）包括纳米结构增强材料（20,21）。本发明还涉及一种生产组装的结构复合材料部件（5）的飞行器结构的方法，其在所述组装之前被固化或半固化。

7. 发明申请

WO2013089598A1 AN AIRCRAFT STRUCTURE WITH STRUCTURAL NON-FIBER REINFORCING BONDING RESIN LAYER 审中-公开
标题翻译：结构非纤维增强粘结树脂层的飞机结构
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
申请人： SAAB AB , GRANKÄLL, Tommy , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn
发明人： GRANKÄLL, Tommy , HALLANDER, Per , PETERSSON, Mikael , WEIDMANN, Björn
IPC分类号： B64C3/20 , B29C65/02 , B29C65/48 , B29C70/54 , B64C1/12 , B64C3/24 , B29L31/30
CPC分类号： 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
摘要： 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.
摘要翻译：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。

8. 发明申请

WO2012099512A1 A COMPOSITE ARTICLE AND A METHOD OF FORMING A COMPOSITE ARTICLE 审中-公开
标题翻译：一种复合材料和一种复合材料的形成方法
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
申请人： SAAB AB , GRANKÄLL, Tommy , HALLANDER, Per , LUNDBERG, Anders , NYMAN, Tonny , WEIDMANN, Björn , PETERSSON, Mikael
发明人： GRANKÄLL, Tommy , HALLANDER, Per , LUNDBERG, Anders , NYMAN, Tonny , WEIDMANN, Björn , PETERSSON, Mikael
IPC分类号： B29C70/20 , B29C70/34 , B29C70/88 , B32B5/26
CPC分类号： B32B5/26 , B29C70/222 , B29C70/30 , B29C70/342 , B29C70/46 , B32B2250/05 , B32B2250/20 , B32B2260/023 , Y10T428/24124
摘要： 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.
摘要翻译：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.

9. 发明申请

WO2014031043A1 A REINFORCED STRUCTURE AND A METHOD FOR MANUFACTURING A REINFORCED STRUCTURE 审中-公开
标题翻译：加固结构和制造加固结构的方法
公开(公告)号：WO2014031043A1
公开(公告)日：2014-02-27
申请号：PCT/SE2012/050890
申请日：2012-08-21
申请人： SAAB AB , GRANKÄLL, Tommy , GUSTAVSSON, Stefan , HALLANDER, Per , LUNDBERG, Anders , PETERSSON, Mikael , WEIDMANN, Björn
发明人： GRANKÄLL, Tommy , GUSTAVSSON, Stefan , HALLANDER, Per , LUNDBERG, Anders , PETERSSON, Mikael , WEIDMANN, Björn
IPC分类号： B29C70/08 , B29C70/30 , B29D99/00 , B64C3/18
CPC分类号： B29C70/342 , B29D99/0007 , B29D99/0014 , B64C2001/0072 , Y02T50/43
摘要： The present invention relates to a reinforced structure (1) and a method for manufacturing a reinforced structure (1) of composite material. The reinforced structure (1) comprises a stiffening element (2) which is attached to the concave surface (37) of a shell element (3). The stiffening element (2) comprises a first profile (5A) and a second profile (5B) connected to each other and forming a web (9). The stiffening element (2) further comprises a reinforcing element (7) of composite material having at least one forming bulge (21) on each of its respective sides (31and 33). The forming bulges (21) extend from an outer edge (27) of the reinforcing element (7) to an inner edge (29) of reinforcing element (7). The height of the at least two forming bulges (21) is highest at the outer edge (27), tapers towards the inner edge (29) and is levelled out at the inner edge (29). The reinforcing element (7) is positioned between the first profile (5A) and the second profile (5B) and forms the web (9) of the stiffening element (2).
摘要翻译：本发明涉及一种增强结构（1）和一种用于制造复合材料的增强结构（1）的方法。加强结构（1）包括附接到壳元件（3）的凹面（37）的加强元件（2）。加强元件（2）包括彼此连接并形成网（9）的第一轮廓（5A）和第二轮廓（5B）。加强元件（2）还包括复合材料的增强元件（7），其在其各自侧面（31和33）上具有至少一个成形凸起（21）。成形凸起（21）从加强元件（7）的外边缘（27）延伸到加强元件（7）的内边缘（29）。至少两个成形凸缘（21）的高度在外边缘（27）处最高，朝着内边缘（29）逐渐变细，并在内边缘（29）处平整。加强元件（7）定位在第一轮廓（5A）和第二轮廓（5B）之间并且形成加强元件（2）的腹板（9）。

10. 发明申请

WO2011062527A1 COMPOSITE STRUCTURE TOOL 审中-公开
标题翻译：复合结构工具
公开(公告)号：WO2011062527A1
公开(公告)日：2011-05-26
申请号：PCT/SE2009/051301
申请日：2009-11-17
申请人： SAAB AB , GRANKÄLL, Tommy , LUNDBERG, Anders , ANDERSSON, Jan , PETERSSON, Mikael , WEIDMANN, Björn , WAARA, Jan , HALLANDER, Per
发明人： GRANKÄLL, Tommy , LUNDBERG, Anders , ANDERSSON, Jan , PETERSSON, Mikael , WEIDMANN, Björn , WAARA, Jan , HALLANDER, Per
IPC分类号： B29C33/40 , B29C33/38 , B29C70/54
CPC分类号： B29C33/0011 , B29C33/3842 , B29C33/40 , B29C33/565 , B29C70/00 , B29L2031/3082
摘要： The present invention regards a method of producing a forming tool and the forming tool for forming an article, the forming tool (1) comprises a composite face sheet (7) having a forming surface (29) and an inner surface (17) opposite the forming surface (29), and further comprises a support structure being attached to the inner surface (17) of the composite face sheet (7). The support structure comprises a support shell (9, 9', 9") of composite having a first surface (27) facing the inner surface (17) of the composite face sheet (7) and having a second surface (28) opposite the first surface (27), the support structure further comprises distance members (11, 31), and the support shell (9, 9', 9") is fixed at a distance from the composite face (7) sheet by means of the distance members (11, 31).
摘要翻译：本发明涉及一种生产成形工具的方法和用于形成制品的成形工具，该成形工具（1）包括具有成形表面（29）的复合面板（7）和与其相对的内表面（17）形成表面（29），并且还包括附接到复合面板（7）的内表面（17）的支撑结构。支撑结构包括具有面向复合面板（7）的内表面（17）的第一表面（27）的复合材料的支撑壳（9,9'，9“），并且具有与第二表面相对的第二表面第一表面（27），支撑结构还包括距离构件（11,31），并且支撑壳体（9,9'，9“）通过距离复合面（7）片材一定距离固定成员（11,31）。

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