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11. 发明授权

US09701067B2 Method of laying up prepreg plies on contoured tools using a deformable carrier film 有权
公开(公告)号：US09701067B2
公开(公告)日：2017-07-11
申请号：US14048009
申请日：2013-10-07
申请人： The Boeing Company
发明人： Robert D. Hawkins , Kurtis S. Willden , Andrew E. Modin , Edoardo Depase , Michael L. Glain , Benjamin Adam Mussi , Max U. Kismarton
IPC分类号： B29C70/20 , B29C70/02 , B29C70/54 , B29C70/30
CPC分类号： B29C70/021 , B29C70/20 , B29C70/30 , B29C70/541
摘要： A method is presented. The method comprises identifying a desired shape of a ply on a tool, in which the ply has a fiber orientation; identifying a cut shape for the ply, in which the cut shape is different than the desired shape; cutting a composite prepreg ply to have the cut shape, the composite prepreg ply having the fiber orientation; using a deformable carrier to apply the composite prepreg ply having the cut shape to the tool such that the composite prepreg ply has the desired shape on the tool.

12. 发明申请

US20150338325A1 UNIVERSAL GRIP SYSTEM 有权
标题翻译：通用GRIP系统
公开(公告)号：US20150338325A1
公开(公告)日：2015-11-26
申请号：US14286926
申请日：2014-05-23
申请人： The Boeing Company
发明人： Max U. Kismarton
IPC分类号： G01N3/02 , B25B5/08 , B25B5/02 , B25B5/00
CPC分类号： G01N3/02 , B25B5/003 , B25B5/02 , B25B5/08 , G01N3/04 , G01N2203/0447
摘要： Provided are universal grip systems and method of using universal grip systems to test coupons. According to various examples, a universal grip system includes two grips and two guide posts for supporting the two grips and allowing the two grips to move with respect to each other. Each grip may include one or two wedges. The wedges are used to engage the coupons during testing and provide anti-buckling support and/or anti-rotation support. The wedges are slidably coupled within corresponding grips, which allows the universal grip system to engage and disengage the coupons by moving one grip with respect to another. The grips may be constructed from thermally neutral materials, such as invar 36. The grips may thermally isolated from the guide posts by, for example, a set of spacers disposed between the grips and linear bearing slidably coupled to the guide posts.
摘要翻译：提供通用抓握系统和使用通用握把系统来测试试样的方法。根据各种示例，通用抓握系统包括两个把手和两个支柱，用于支撑两把手并允许两把手相对于彼此移动。每个把手可以包括一个或两个楔子。在测试期间楔子用于接合试样，并提供抗弯曲支撑和/或抗旋转支撑。楔形件可滑动地联接在相应的夹具内，这允许万能夹具系统通过相对于另一个夹持器移动一个把手来接合和脱离优惠券。夹具可以由热中性材料（例如内耳36）构成。夹具可以通过例如设置在夹具和可滑动地联接到引导柱的线性轴承之间的一组间隔件与引导柱热隔离。

13. 发明申请

US20150020603A1 Apparatus, System and Method for Compression Testing of Test Specimens 有权
标题翻译：试验样品压缩试验装置，系统及方法
公开(公告)号：US20150020603A1
公开(公告)日：2015-01-22
申请号：US13947050
申请日：2013-07-20
申请人： The Boeing Company
发明人： Max U. Kismarton , Kenneth H. Griess
IPC分类号： G01N3/02
CPC分类号： G01N3/02 , G01M5/005 , G01M5/0091 , G01M11/081 , G01N3/04 , G01N3/08 , G01N2203/0003 , G01N2203/001 , G01N2203/0019 , G01N2203/027 , G01N2203/0282 , G01N2203/0447 , G01N2203/0641
摘要： There is provided an apparatus for compression testing. The apparatus has a base assembly having an end load element attached to the base assembly, the base assembly being rigid. The apparatus has a support assembly attached to the base assembly, and having a plurality of window portions. The apparatus has a core assembly installed within the support assembly, the core assembly being crushable and configured to protect the support assembly and the base assembly from fracture loads generated during compression testing. The base assembly, the support assembly, and the core assembly together form an apparatus for compression testing of a test specimen having a notch portion. The apparatus is configured for use with an optical strain measurement system. When the test specimen is installed in the support assembly, the test specimen and the notch portion are visible to the optical strain measurement system through the plurality of window portions.
摘要翻译：提供了一种用于压缩测试的装置。该装置具有底座组件，其具有附接到基座组件的端部负载元件，该基座组件是刚性的。该装置具有附接到基座组件的支撑组件，并具有多个窗口部分。该装置具有安装在支撑组件内的芯组件，该芯组件可压碎并构造成保护支撑组件和基座组件免受压缩试验期间产生的断裂负荷。基座组件，支撑组件和芯组件一起形成用于具有切口部分的测试样品的压缩测试的装置。该装置被配置为与光学应变测量系统一起使用。当试样被安装在支撑组件中时，试样和切口部分对于光学应变测量系统通过多个窗口部分是可见的。

14. 发明申请

US20140227479A1 COMPOSITE LAMINATE INCLUDING BETA-REINFORCING FIBERS 有权
标题翻译：包括增强纤维的复合层压板
公开(公告)号：US20140227479A1
公开(公告)日：2014-08-14
申请号：US14252764
申请日：2014-04-14
申请人： The Boeing Company
发明人： Max U. Kismarton
IPC分类号： B32B5/12 , B64C1/06
CPC分类号： B32B5/12 , B29C65/562 , B29C65/564 , B29C66/112 , B29C66/1122 , B29C66/131 , B29C66/474 , B29C66/524 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C70/202 , B29C70/207 , B29C70/228 , B29C70/30 , B29K2101/00 , B29K2307/00 , B29K2707/04 , B29L2031/3076 , B32B1/00 , B32B5/26 , B32B5/28 , B32B2250/20 , B32B2260/023 , B32B2260/046 , B32B2262/106 , B64C1/064 , B64C1/12 , B64C3/182 , B64C3/26 , B64C2001/0072 , Y02T50/43 , Y10T428/24124 , B29K2307/04
摘要： A composite laminate comprises a plurality of plies of reinforcing fibers. At least some of the plies have reinforcing fibers oriented at ±α with respect to an axis of primary loading, where α is between 2 and 12 degrees. At least some of the plies have reinforcing fibers oriented at ±β with respect to the axis of primary loading, where β is between 50 and 85 degrees.
摘要翻译：复合层压板包括多层增强纤维。至少一些帘布层具有相对于主负载轴线以±α取向的增强纤维，其中α在2和12度之间。至少一些帘布层具有以±＆bgr取向的增强纤维; 相对于主负载轴，其中＆bgr; 在50和85度之间。

15. 发明授权

US12049048B2 Method for high rate production of composite laminate structures 有权
公开(公告)号：US12049048B2
公开(公告)日：2024-07-30
申请号：US17814992
申请日：2022-07-26
申请人： The Boeing Company
发明人： Max U. Kismarton
IPC分类号： B29C70/34 , B29C70/54 , B29L31/30
CPC分类号： B29C70/34 , B29C70/545 , B29L2031/3076
摘要： Multi-ply composite charges are laid up by a multi-head laminator in a single pass, enabling high rate production of composite laminate structures such as stringers.

16. 发明授权

US11969953B2 Prepreg charge optimized for forming contoured composite laminate structures 有权
公开(公告)号：US11969953B2
公开(公告)日：2024-04-30
申请号：US17814996
申请日：2022-07-26
申请人： The Boeing Company
发明人： Max U. Kismarton
IPC分类号： B29C70/20 , B29B11/16 , B29L31/30
CPC分类号： B29C70/202 , B29B11/16 , B29L2031/3076
摘要： A composite charge used to compression form a stringer comprises multiple plies of unidirectional, prepreg having various fiber orientations. Certain of the plies have a pattern of angled cuts allowing the plies to stretch both longitudinally and transversely during forming, thereby reducing ply wrinkling in contoured areas of the stringer.

17. 发明授权

US10828851B2 Slip sheet with compensation surface 有权
公开(公告)号：US10828851B2
公开(公告)日：2020-11-10
申请号：US15662969
申请日：2017-07-28
申请人： The Boeing Company
发明人： Max U. Kismarton , Karl Marius Nelson , Geoffrey Allen Butler
IPC分类号： B32B41/00 , B29C70/54 , B29D99/00 , B29C70/30 , B29C70/34 , B29L31/30
摘要： A method and an apparatus are presented. The method locally compensates for cure related deformations in a composite skin by laying up a composite material on a compensation surface of a slip sheet designed to form a modified outer mold line different from a designed shape, wherein the slip sheet is held against a forming surface of a layup tool, wherein the forming surface is designed to form an outer mold line of the designed shape.

18. 发明授权

US10322564B2 Thermoplastic and titanium sandwich structures 有权
公开(公告)号：US10322564B2
公开(公告)日：2019-06-18
申请号：US15292089
申请日：2016-10-12
申请人： The Boeing Company
发明人： Marc Rollo Matsen , Jeffery Lee Marcoe , Max U. Kismarton , Paul Stevenson Gregg , Lee Charles Firth
IPC分类号： B32B15/08 , B29D99/00 , B29C70/44 , B29C33/06 , B29C35/02 , B29C35/08 , B32B3/12 , B29L31/30 , B29K101/12
摘要： A method and apparatus for forming a sandwich structure is presented. A sandwich structure comprises a metallic core layer and a thermoplastic layer on a first side of the metallic core layer. The thermoplastic layer is consolidated against the first side of the metallic core layer.

19. 发明授权

US10317322B2 Combined loading in composite materials 有权
公开(公告)号：US10317322B2
公开(公告)日：2019-06-11
申请号：US14547844
申请日：2014-11-19
申请人： THE BOEING COMPANY
发明人： Max U. Kismarton , Samuel Eric Cregger
IPC分类号： G01N3/08 , G01N3/24 , G06F17/50
摘要： A method for determining material failure that includes the steps of: fabricating a coupon made of a material; applying first force and second forces on the coupon, where the second force is different than the first force; and characterizing a material failure due to the application of the first force and the second force to the coupon.

20. 发明授权

US10131417B2 Hybrid carbon/fiberglass structural component for an aircraft 有权
公开(公告)号：US10131417B2
公开(公告)日：2018-11-20
申请号：US15495152
申请日：2017-04-24
申请人： The Boeing Company
发明人： Max U. Kismarton , Devin E. Knowles , Francis E. Andrews
IPC分类号： B32B5/12 , B64C1/18 , B64C1/06 , D01F9/12 , C03C13/00 , B64C1/00
摘要： A hybrid carbon/fiberglass structural component or beam for an aircraft is constructed with layers of strips of glass fibers interspersed with layers of strips of unidirectional carbon fibers where the carbon fibers are oriented only in alignment with or along the longitudinal direction of the length of the beam thereby adding strength and stiffness to the beam while reducing weight and manufacturing costs.

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