Tool fabrication for composite forming of aircraft winglet using multi-point dieless forming
Flexible forming technology such as Multi-point dieless forming (MDF) has benefits for the sheet metal field because it can implement a variety of mold shapes using a single apparatus. Generally, aircraft winglets are fabricated using composite materials. To make composite material, a curing process...
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Published in | Journal of mechanical science and technology Vol. 30; no. 5; pp. 2203 - 2210 |
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Main Authors | , , , , |
Format | Journal Article |
Language | English |
Published |
Seoul
Korean Society of Mechanical Engineers
01.05.2016
Springer Nature B.V 대한기계학회 |
Subjects | |
Online Access | Get full text |
ISSN | 1738-494X 1976-3824 |
DOI | 10.1007/s12206-016-0428-7 |
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Abstract | Flexible forming technology such as Multi-point dieless forming (MDF) has benefits for the sheet metal field because it can implement a variety of mold shapes using a single apparatus. Generally, aircraft winglets are fabricated using composite materials. To make composite material, a curing process is needed. Therefore, it is necessary to manufacture the mold for the curing process in the fabrication composite materials. For mold manufacturing, MDF technology has the advantages of low manufacturing cost and high uniformity in mold thickness compared with conventional machining processes. In this study, numerical simulations are carried out to evaluate the feasibility of MDF process for the production of winglet molds. The objective surface is bigger than actual MDF apparatus; it is divided into 8 segments to match the dimensions of the apparatus. Experiments are conducted under the same conditions as a numerical simulation. To confirm the forming accuracy, curvature profiles of simulation and experiment results are compared with the target curvature. Eight formed segments are assembled into one winglet mold. As a result, the applicability of the MDF process to the fabrication of aircraft winglet molds is verified through this research. |
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AbstractList | Flexible forming technology such as Multi-point dieless forming (MDF) has benefits for the sheet metal field because it can implement a variety of mold shapes using a single apparatus. Generally, aircraft winglets are fabricated using composite materials. To make composite material, a curing process is needed. Therefore, it is necessary to manufacture the mold for the curing process in the fabrication composite materials. For mold manufacturing, MDF technology has the advantages of low manufacturing cost and high uniformity in mold thickness compared with conventional machining processes. In this study, numerical simulations are carried out to evaluate the feasibility of MDF process for the production of winglet molds. The objective surface is bigger than actual MDF apparatus; it is divided into 8 segments to match the dimensions of the apparatus. Experiments are conducted under the same conditions as a numerical simulation. To confirm the forming accuracy, curvature profiles of simulation and experiment results are compared with the target curvature.
Eight formed segments are assembled into one winglet mold. As a result, the applicability of the MDF process to the fabrication of aircraft winglet molds is verified through this research. KCI Citation Count: 0 Flexible forming technology such as Multi-point dieless forming (MDF) has benefits for the sheet metal field because it can implement a variety of mold shapes using a single apparatus. Generally, aircraft winglets are fabricated using composite materials. To make composite material, a curing process is needed. Therefore, it is necessary to manufacture the mold for the curing process in the fabrication composite materials. For mold manufacturing, MDF technology has the advantages of low manufacturing cost and high uniformity in mold thickness compared with conventional machining processes. In this study, numerical simulations are carried out to evaluate the feasibility of MDF process for the production of winglet molds. The objective surface is bigger than actual MDF apparatus; it is divided into 8 segments to match the dimensions of the apparatus. Experiments are conducted under the same conditions as a numerical simulation. To confirm the forming accuracy, curvature profiles of simulation and experiment results are compared with the target curvature. Eight formed segments are assembled into one winglet mold. As a result, the applicability of the MDF process to the fabrication of aircraft winglet molds is verified through this research. |
Author | Ku, Tae-Wan Kang, Beom-Soo Park, Ji-Woo Kim, Kwang-Ho Kim, Jeong |
Author_xml | – sequence: 1 givenname: Ji-Woo surname: Park fullname: Park, Ji-Woo organization: Department of Aerospace Engineering, Pusan National University – sequence: 2 givenname: Tae-Wan surname: Ku fullname: Ku, Tae-Wan organization: ERC/ITAF, Pusan National University – sequence: 3 givenname: Jeong surname: Kim fullname: Kim, Jeong organization: Department of Aerospace Engineering, Pusan National University – sequence: 4 givenname: Kwang-Ho surname: Kim fullname: Kim, Kwang-Ho organization: R&D Center, Steel Flower Co. Ltd – sequence: 5 givenname: Beom-Soo surname: Kang fullname: Kang, Beom-Soo email: bskang@pusan.ac.kr organization: Department of Aerospace Engineering, Pusan National University |
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CitedBy_id | crossref_primary_10_1007_s00170_018_3155_7 crossref_primary_10_1016_j_ijmecsci_2019_04_020 crossref_primary_10_1016_j_ijmecsci_2018_11_002 crossref_primary_10_1007_s00170_017_1372_0 crossref_primary_10_1007_s12289_023_01790_z crossref_primary_10_1016_j_ijmecsci_2018_05_005 |
Cites_doi | 10.1007/s00170-014-5859-7 10.1007/s12206-009-1119-4 10.5228/KSTP.2013.22.4.196 10.1016/j.compscitech.2004.12.015 10.5228/KSPP.2010.19.1.017 10.1016/S1359-8368(99)00034-7 10.5228/KSPP.2008.17.8.570 10.1007/s12541-012-0236-7 10.1007/s12541-014-0610-8 10.1016/j.paerosci.2005.02.004 10.1007/s00170-009-2290-6 10.2514/3.57531 10.1201/b14889 |
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Keywords | Aircraft winglet Numerical simulation and experiments Composite mold fabrication Multi-point dieless forming |
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Technol. doi: 10.1016/j.compscitech.2004.12.015 – volume-title: NASA TN D-8260 year: 1976 ident: 428_CR17 – volume: 19 start-page: 17 issue: 1 year: 2010 ident: 428_CR5 publication-title: Trans. Mater. Process. doi: 10.5228/KSPP.2010.19.1.017 – volume: 48 start-page: 45 year: 2010 ident: 428_CR4 publication-title: J. Adv. Manuf. Technol. doi: 10.1007/s00170-009-2290-6 – volume: 41 start-page: 143 year: 2005 ident: 428_CR18 publication-title: Prog. Aerosp. Sci. doi: 10.1016/j.paerosci.2005.02.004 – volume: 13 start-page: 1797 issue: 10 year: 2012 ident: 428_CR6 publication-title: J. Precis. Engine. Manuf. doi: 10.1007/s12541-012-0236-7 – volume-title: Principles of composite material mechanics year: 2011 ident: 428_CR13 doi: 10.1201/b14889 – volume-title: Composite materials for aircraft structures year: 2004 ident: 428_CR10 – ident: 428_CR20 |
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SubjectTerms | Aircraft Composite materials Computer simulation Control Curing Curvature Dieless Dynamical Systems Engineering Feasibility studies Forming Industrial and Production Engineering Machining MDF Mechanical Engineering Metal sheets Molds Segments Vibration Winglets 기계공학 |
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Title | Tool fabrication for composite forming of aircraft winglet using multi-point dieless forming |
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