公开(公告)号：KR100775888B1

公开(公告)日：2007-11-15

申请号：KR1020060121890

申请日：2006-12-05

Applicant: 한국항공우주연구원

Inventor： 공철원 ,  이종웅 ,  남기원 ,  장영순 ,  이영무

IPC: G01N25/72

CPC classification number: G01N25/72 ,  G01K13/00

Abstract: A nondestructive inspection device having a composite material structure is provided to remarkably reduce the inspection cost by detecting even a defect of a porous material. A nondestructive inspection device includes a temperature regulating unit(30), a first temperature sensor(20a), a second temperature sensor(20b), and a computer(40). The temperature regulating unit includes a heating wire attached to one side of a complex structure and regulates the temperature of the complex structure to have waves having a predetermined period. The first temperature sensor is provided between the heating wire and the complex structure. The second temperature sensor is provided on the other side of the complex structure to which the heating wire is attached. The computer includes an information setting section, a control section, and a memory section.

Abstract translation: 提供具有复合材料结构的非破坏性检查装置，通过检测多孔材料的缺陷来显着降低检查成本。 无损检测装置包括温度调节单元（30），第一温度传感器（20a），第二温度传感器（20b）和计算机（40）。 温度调节单元包括附着在复合结构的一侧的加热线，并且调节复合结构的温度以具有预定周期的波。 第一温度传感器设置在加热线和复合结构之间。 第二温度传感器设置在加热线所附接的复合结构的另一侧。 计算机包括信息设置部分，控制部分和存储部分。

公开(公告)号：KR1020140084990A

公开(公告)日：2014-07-07

申请号：KR1020120155057

申请日：2012-12-27

Applicant: 한국항공우주연구원

Inventor： 남기원 ,  공철원 ,  장영순

IPC: G01N3/08 ,  G01N3/02

CPC classification number: G01N3/08 ,  B25B11/02 ,  G01N3/02 ,  G01N2203/0017 ,  G01N2203/04

Abstract: The present invention relates to a jig for a tensile test of a composite laminated structure, whereby is used to conduct a tensile test of a composite laminated structure (1) including a honeycomb core (10) and composites (30) attached to the top and bottom of the honeycomb core (10) respectively using an adhesive (20). The jig for a tensile test of a composite laminated structure comprises: a first tensile fixture (100) combined with a composite (30) attached to the top of a honeycomb core (10); and a second tensile fixture (200) combined with a composite (30) attached to the bottom of the honeycomb core (10). The first and second tensile fixtures (100, 200) are made of the same material as the composite (30). In addition, a tensile test of the composite laminated structure (1) can be conducted by extending the first and second tensile fixtures (100, 200) in a vertical direction.

Abstract translation: 本发明涉及一种用于复合叠层结构的拉伸试验的夹具，由此用于进行包括蜂窝芯（10）和复合材料（30）的复合层压结构（1）的拉伸试验，所述复合层压结构（1）附接到顶部和 蜂窝芯（10）的底部分别使用粘合剂（20）。 用于复合层压结构的拉伸试验的夹具包括：与附接到蜂窝芯（10）的顶部的复合材料（30）组合的第一拉伸夹具（100）。 以及与附接到蜂窝芯（10）的底部的复合材料（30）组合的第二拉伸夹具（200）。 第一和第二拉伸夹具（100,200）由与复合材料（30）相同的材料制成。 此外，复合层压结构（1）的拉伸试验可以通过沿垂直方向延伸第一和第二拉伸固定装置（100,200）来进行。

公开(公告)号：KR101376499B1

公开(公告)日：2014-03-25

申请号：KR1020120146076

申请日：2012-12-14

Applicant: 한국항공우주연구원

Inventor： 공철원 ,  남기원 ,  장영순

IPC: B64C1/12 ,  B32B3/12

CPC classification number: B32B3/12 ,  B32B2250/40 ,  B32B2305/024 ,  B32B2305/34 ,  B32B2307/202 ,  B32B2605/18

Abstract: The present invention relates to a laminated composite structure having an electric bonding insert, including: a honeycomb core (100) An insertion hole (110) perforated in a heightwise direction; an electric boding insert (200) which is inserted to the insertion hole (110), and which can adjusted of the length in the heightwise direction of the honeycomb core (110); and a composite (300) which is adhered to one and the other sides of the heightwise direction of the honeycomb core (100). All of the above components are made of conductive material.

Abstract translation: 本发明涉及具有电接合插入物的层压复合结构体，其包括：蜂窝芯（100），在高度方向上穿孔的插入孔（110） 电插入插入件（200），其插入到插入孔（110）中，并且可以调节蜂窝芯（110）的高度方向上的长度; 以及粘合到蜂窝芯（100）的高度方向的一侧和另一侧的复合体（300）。 所有上述组件均由导电材料制成。