KR101523202B1 - Manufaction method of volt for spacecraft - Google Patents
Manufaction method of volt for spacecraft Download PDFInfo
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- KR101523202B1 KR101523202B1 KR1020140137298A KR20140137298A KR101523202B1 KR 101523202 B1 KR101523202 B1 KR 101523202B1 KR 1020140137298 A KR1020140137298 A KR 1020140137298A KR 20140137298 A KR20140137298 A KR 20140137298A KR 101523202 B1 KR101523202 B1 KR 101523202B1
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- bolt
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- 238000000034 method Methods 0.000 title claims abstract description 44
- 238000004519 manufacturing process Methods 0.000 claims abstract description 18
- 239000000463 material Substances 0.000 claims description 25
- 230000032683 aging Effects 0.000 claims description 23
- 238000010438 heat treatment Methods 0.000 claims description 16
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 12
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 11
- 238000010273 cold forging Methods 0.000 claims description 10
- 238000003483 aging Methods 0.000 claims description 9
- 239000000126 substance Substances 0.000 claims description 7
- QTBSBXVTEAMEQO-UHFFFAOYSA-N Acetic acid Chemical compound CC(O)=O QTBSBXVTEAMEQO-UHFFFAOYSA-N 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- 229910052759 nickel Inorganic materials 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- 229910001873 dinitrogen Inorganic materials 0.000 claims description 5
- 239000012535 impurity Substances 0.000 claims description 5
- 229910052760 oxygen Inorganic materials 0.000 claims description 5
- 239000001301 oxygen Substances 0.000 claims description 5
- 229910052710 silicon Inorganic materials 0.000 claims description 5
- 239000010703 silicon Substances 0.000 claims description 5
- 239000010936 titanium Substances 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 4
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims description 4
- QAOWNCQODCNURD-UHFFFAOYSA-N Sulfuric acid Chemical compound OS(O)(=O)=O QAOWNCQODCNURD-UHFFFAOYSA-N 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 239000011651 chromium Substances 0.000 claims description 4
- 229910052717 sulfur Inorganic materials 0.000 claims description 4
- 239000011593 sulfur Substances 0.000 claims description 4
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052796 boron Inorganic materials 0.000 claims description 3
- 239000010941 cobalt Substances 0.000 claims description 3
- 229910017052 cobalt Inorganic materials 0.000 claims description 3
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- NBIIXXVUZAFLBC-UHFFFAOYSA-N Phosphoric acid Chemical compound OP(O)(O)=O NBIIXXVUZAFLBC-UHFFFAOYSA-N 0.000 claims 2
- 229910000831 Steel Inorganic materials 0.000 claims 2
- 239000010959 steel Substances 0.000 claims 2
- 229910000838 Al alloy Inorganic materials 0.000 claims 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims 1
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims 1
- 229910000147 aluminium phosphate Inorganic materials 0.000 claims 1
- 238000005304 joining Methods 0.000 claims 1
- 229910052748 manganese Inorganic materials 0.000 claims 1
- 239000011572 manganese Substances 0.000 claims 1
- 229910052751 metal Inorganic materials 0.000 claims 1
- 239000002184 metal Substances 0.000 claims 1
- 229910052698 phosphorus Inorganic materials 0.000 claims 1
- 239000011574 phosphorus Substances 0.000 claims 1
- 230000000704 physical effect Effects 0.000 abstract description 10
- 230000000052 comparative effect Effects 0.000 description 12
- 238000002360 preparation method Methods 0.000 description 7
- 238000005096 rolling process Methods 0.000 description 6
- 238000002161 passivation Methods 0.000 description 5
- 238000003825 pressing Methods 0.000 description 4
- 238000007429 general method Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 239000011825 aerospace material Substances 0.000 description 2
- 229910052797 bismuth Inorganic materials 0.000 description 2
- JCXGWMGPZLAOME-UHFFFAOYSA-N bismuth atom Chemical compound [Bi] JCXGWMGPZLAOME-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K1/00—Making machine elements
- B21K1/44—Making machine elements bolts, studs, or the like
- B21K1/46—Making machine elements bolts, studs, or the like with heads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
- B21H3/00—Making helical bodies or bodies having parts of helical shape
- B21H3/02—Making helical bodies or bodies having parts of helical shape external screw-threads ; Making dies for thread rolling
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C38/00—Ferrous alloys, e.g. steel alloys
- C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
- C22C38/40—Ferrous alloys, e.g. steel alloys containing chromium with nickel
- C22C38/58—Ferrous alloys, e.g. steel alloys containing chromium with nickel with more than 1.5% by weight of manganese
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
Abstract
Description
본 발명은 인공위성 등과 같은 우주선에 사용되는 볼트를 제조하는 발명에 관한 것으로서, 그 제조공정 시간을 획기적으로 줄이면서도 AMS 5731L 규격 등과 같은 고스펙을 만족하는 우주선용 볼트를 제공할 수 있는 발명에 관한 것이다.
BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an invention for manufacturing a bolt used in a spacecraft such as a satellite and the like, and it is an object of the present invention to provide a spacecraft bolt satisfying high specifications such as the AMS 5731L standard, .
인공위성과 같은 우주용 비행체에 사용되는 소재, 부품은 혹독한 환경을 견딜 수 있도록 고품질, 고스펙의 요건을 만족해야 하며, 우주용 비행체에 납품되는 부품을 제조하는 방법은 대부분 노하우 등으로 비공개 상태로 제조되고 있다. 그리고, 우주용 비행체에 사용되는 볼트에 대해서는 규격화시키고 있는데, SAE가 발행하는 우주 항공용 재료 시방서인 AMS(aerospace material specifications)를 통해 규격화하고 있다.Materials and components used in aerospace vehicles such as satellites must meet the requirements of high quality and high specification to withstand harsh environments. Most of the methods of manufacturing parts supplied to spacecraft are made in private . In addition, the bolts used in aerospace aviation are standardized through aerospace material specifications (AMS), an aerospace material specification issued by SAE.
기존에는 이와 같이 우주용 비행체에 사용되는 볼트 등을 제조시에는 그 사용환경 특성상 고스펙을 만족시키기 위해서 냉간단조->용체화->시효경화->화학연마->나사로링->부동태처리 등의 공정을 수행하여 제조하였으며, 그 제조공정이 복잡하여 생산성이 떨어지는 문제가 있었다.In the past, when manufacturing bolts used in aerospace vehicles, in order to satisfy high specifications due to its use environment characteristics, cold forging-> solution-> age hardening-> chemical polishing-> screwing-> passivation And the manufacturing process is complicated, resulting in a problem of low productivity.
최근 항공우주산업 분야에 대한 투자가 급증하고 있으나, 이에 사용되는 부품에 대한 국내 자체 기술이 확보되지 못해서 외국 기술에 대한 의존도가 매우 높은 상황이며, 이에 따라 항공우주산업 분야에서 사용되는 필수 부품들에 대한 국내 연구 및 이에 대한 투자가 시급한 실정이다.
Recently, the investment in the aerospace industry is increasing rapidly, but the domestic technology is not secured for the used parts, so it is highly dependent on the foreign technology. Therefore, the essential parts used in the aerospace industry It is urgent to invest in domestic research and investment.
기존의 우주선용 볼트의 경우, 고스펙을 만족시키기 위해서 복잡다단한 공정을 수행하여야 했기 때문에 가격이 고가이고, 생산성이 떨어지는 문제가 있었으며, 이에 본 발명자들은 오랜 연구 끝에, 제조공정을 간소화시키면서도 우주선용 볼트로서 요구되는 물성의 스펙을 만족시킬 수 있는 방법을 알게 되어 본 발명을 완성하게 되었다.
In the case of conventional spacecraft bolts, a complicated multi-step process has to be performed in order to satisfy the high specification, so that the cost is high and the productivity is low. The inventors of the present invention, after a long period of research, The present inventors have found a method of satisfying the specification of physical properties required as a bolt, thereby completing the present invention.
상기 과제를 해결하기 위한 본 발명은 우주선용 볼트를 제조하는 방법에 관한 것으로서, 특정 성분을 특정 비율로 포함하는 볼트용 소재를 냉간단조시키는 단계; 냉간단조한 볼트용 소재를 700 ~ 750℃ 하에서 15 ~ 17시간 동안 진공열처리를 수행하여 시효경화시킨 볼트를 제조하는 단계; 시효경화시킨 볼트를 나사전조가공하는 단계; 및 나사전조가공한 볼트를 부동태처리하는 단계;를 포함하는 공정을 수행하여 우주선용 볼트를 제조하는 것을 특징으로 한다.According to an aspect of the present invention, there is provided a method of manufacturing a spacecraft bolt, the method comprising: cold-forging a bolt material containing a specific component in a specific ratio; Subjecting the cold forged bolt material to vacuum heat treatment at 700 to 750 ° C for 15 to 17 hours to produce an aged hardened bolt; Screw aging the aged bolt; And passivating the threaded bolts to manufacture a spacecraft bolt.
또한, 본 발명은 상기 제조방법에 의해 제조된 고스펙의 우주선용 볼트를 제공할 수 있는 발명에 관한 것이다.
Further, the present invention relates to an invention capable of providing a high-specification spacecraft bolt manufactured by the above manufacturing method.
본 발명은 제조방법은 열처리 공정 중 용체화 공정을 수행하지 않으면서도 인공위성 등과 같은 우주선에 사용되는 고스펙의 물성을 만족하는 우주선용 볼트를 제조할 수 있으며, 구체적으로는 우수한 인장강도, 항복강도, 신장율, 단면수축률 및 경도를 갖는 우주선용 볼트를 제공할 수 있는 발명에 관한 것이다.
The method of the present invention can manufacture a spacecraft bolt satisfying physical properties of a high specification used for spacecraft such as artificial satellites and the like without performing a solution process during a heat treatment process, Sectional area, shrinkage ratio and hardness of a spacecraft.
도 1은 냉간단조공정을 찍은 사진.
도 2는 냉간단조시킨 볼트용 소재를 볼트크기로 절단하는 사진.
도 3 및 도 4는 부동태 처리한 우주선용 볼트의 사진.Fig. 1 is a photograph of a cold forging process. Fig.
Fig. 2 is a photograph of a bolt-sized material for cold forging; Fig.
Figures 3 and 4 are photographs of passive bolts for spacecrafts.
이하 본 발명에 대하여 더욱 자세하게 설명을 한다.Hereinafter, the present invention will be described in detail.
본 발명은 우주선용 볼트로서, AMS 5731L 규격 등과 같은 고스펙을 만족하는 우주선용 볼트를 제조할 수 있는 발명에 관한 것으로서, 볼트용 소재를 냉간단조시키는 단계; 냉간단조된 볼트용 소재를 진공열처리를 수행하여 시효경화시키는 단계; 시효경화시킨 볼트를 나사전조가공하는 단계; 및 나사전조가공한 볼트를 부동태처리하는 단계;를 포함하는 공정을 수행하는 것을 특징으로 할 수 있다.The present invention relates to a spacecraft bolt, which can manufacture a spacecraft bolt satisfying a high specification such as the AMS 5731L standard, comprising: cold-forging a bolt material; Subjecting the cold forged bolt material to an age hardening by vacuum heat treatment; Screw aging the aged bolt; And a step of passivating the threaded bolts.
본 발명에 있어서, 상기 냉간단조시키는 단계의 볼트는 탄소 0.035 ~ 0.045 중량%, 망간 1.74 ~ 1.76 중량%, 규소 0.19 ~ 0.21 중량%, 황 0.002 ~ 0.004 중량%, 인 0.015 ~ 0.017 중량%, 니켈 24.4 ~ 24.7 중량%, 크롬 14.7 ~ 14.9 중량% 및 몰리브덴 1.23 ~ 1.28 중량%로 포함할 수 있으며, 바람직하게는 탄소 0.038 ~ 0.042 중량%, 망간 1.74 ~ 1.76 중량%, 규소 0.19 ~ 0.21 중량%, 황 0.0025 ~ 0.0035 중량%, 인 0.0155 ~ 0.0165 중량%, 니켈 24.45 ~ 24.60 중량%, 크롬 14.75 ~ 14.85 중량% 및 몰리브덴 1.24 ~ 1.26 중량%로 포함할 수 있고, 더욱 바람직하게는 탄소 0.039 ~ 0.041 중량%, 망간 1.745 ~ 1.755 중량%, 규소 0.19 ~ 0.21 중량%, 황 0.0028 ~ 0.0032 중량%, 인 0.0158 ~ 0.0162 중량%, 니켈 24.50 ~ 24.58 중량%, 크롬 14.75 ~ 14.85 중량% 및 몰리브덴 1.24 ~ 1.26 중량%로 포함할 수 있다.In the present invention, the bolts of the cold forging may comprise 0.035 to 0.045 wt% of carbon, 1.74 to 1.76 wt% of manganese, 0.19 to 0.21 wt% of silicon, 0.002 to 0.004 wt% of sulfur, 0.015 to 0.017 wt% of nickel, Preferably from 0.038% to 0.042% by weight of carbon, from 1.74% to 1.76% by weight of manganese, from 0.19% to 0.21% by weight of silicon, from 0.0025% by weight of sulfur, By weight of carbon, 0.0155 to 0.0165% by weight of nickel, 24.45 to 24.60% by weight of nickel, 14.75 to 14.85% by weight of chromium and 1.24 to 1.26% by weight of molybdenum, more preferably 0.039 to 0.041% By weight of chromium, 1.45 to 1.755% by weight of silicon, 0.19 to 0.21% of silicon, 0.0028 to 0.0032% of sulfur, 0.0158 to 0.0162% of nickel, 24.50 to 24.58% of nickel, 14.75 to 14.85% of chromium and 1.24 to 1.26% of molybdenum .
또한, 상기 볼트는 탄소, 망간, 규소, 황, 인, 니켈, 크롬 및 몰리브덴 외에 기타 성분으로서, 구리(Cu), 코발트(Co), 질소(N), 알루미늄(Al), 티타늄(Ti), 납(Pb), 비스무트(Bi), 붕소(B), 지르코늄(Zr) 및 철(Fe)을 더 포함할 수 있다. 그리고, 이들 기타 성분의 함유량은 구리 0.15 ~ 0.17 중량%, 코발트 0.17 ~ 0.19 중량%, 질소 0.34 ~ 0.38 중량%, 알루미늄 0.12 ~ 0.16 중량%, 티타늄 2.20 ~ 2.30 중량%, 붕소 0.004 ~ 0.010 중량%, 납 0.0001 중량% 이하, 비스무트 0.2 중량% 이하 및 지르코늄 0.005 중량% 이하로 포함할 수 있다.The bolt may be made of at least one of copper (Cu), cobalt (Co), nitrogen (N), aluminum (Al), titanium (Ti) (Pb), bismuth (Bi), boron (B), zirconium (Zr), and iron (Fe). The content of these other components is 0.15 to 0.17 wt% of copper, 0.17 to 0.19 wt% of cobalt, 0.34 to 0.38 wt% of nitrogen, 0.12 to 0.16 wt% of aluminum, 2.20 to 2.30 wt% of titanium, 0.004 to 0.010 wt% of boron, Lead 0.0001 wt% or less, bismuth 0.2 wt% or less, and zirconium 0.005 wt% or less.
본 발명에 있어서, 상기 냉각단조(cold forging)는 당업계에서 사용하는 일반적인 방법을 사용할 수 있으며, 바람직하게는 압출가공 또는 업세팅가공을 통해서 수행할 수 있으며 더욱 바람직하게는 도 1에 사진으로 나타낸 바와 같은 압출가공을 통해 수행할 수 있다. 그리고, 냉간단조를 구체적인 예를 들면, 다이중에 삽입된 소재를 펀치와 녹아웃에 의하여 샌드위치하고, 상기 녹아웃에 소정의 가압력을 부여하고, 펀치에 녹아웃가압력과 성형가압력과의 합보다도 큰 가압력을 부여하여 성형하거나, 또는 다이 중에 삽입된 소재를 펀치와 녹아웃에 의하여 소정의 가압력을 갖고 샌드위치하고, 이 샌드위치한 상태에서 상기 펀치를 회전시키면서 그 펀치에 녹아웃가압력과 성형가압력과의 합보다도 큰 축방향의 가압력을 부여하여 상기 소재를 성형하도록 할 수 있다.In the present invention, the cold forging may be carried out by a general method used in the art, preferably by extrusion or upsetting. More preferably, And can be carried out through an extrusion process such as a bar. Specifically, for example, cold forging is performed by sandwiching a material inserted in a die by punching and knockout, applying a predetermined pressing force to the knockout, and applying a pressing force larger than a sum of a knockout pressure and a molding- Or the material inserted in the die is sandwiched with a predetermined pressing force by a punch and a knock-out, and the punch is rotated in the sandwich state, and a pressing force in the axial direction larger than the sum of the knock- So that the material can be formed.
그리고, 냉간단조를 수행한 볼트용 소재를 원하는 크기로 절단하는 공정을 시효경화시키는 단계 전에 더 수행할 수 있다.Further, the step of cutting the material for a bolt subjected to cold forging to a desired size can be further performed before the age hardening step.
다음으로 시효경화를 수행하는데, 그리고, 시효경화를 수행하기 전의 볼트 소재는 KS B 1003 방법에 의거하여 측정시 인장강도(Tensile strength) 95 ~ 120 kgf/㎟, KS B 1003 방법에 의거하여 측정시 항복강도(yield strength) 40 ~ 55 kgf/㎟ 및 KS B 1003 방법에 의거하여 측정시 신장율(elongation) 45 ~ 60%을 만족할 수 있으며, 바람직하게는 인장강도 98 ~ 110 kgf/㎟, 항복강도 45 ~ 50 kgf/㎟ 및 신장율 46 ~ 55%를 만족할 수 있고, 더욱 바람직하게는 인장강도 100 ~ 105 kgf/㎟, 항복강도 45 ~ 49 kgf/㎟ 및 신장율 47 ~ 52%를 만족할 수 있다.Next, the aging hardening is performed, and before the aging hardening, the bolt material has a tensile strength of 95 to 120 kgf / mm 2 measured according to the KS B 1003 method, and is measured according to the KS B 1003 method A yield strength of 40 to 55 kgf / mm 2 and an elongation of 45 to 60% as measured by the KS B 1003 method, preferably a tensile strength of 98 to 110 kgf / mm 2, a yield strength of 45 To 50 kgf / mm 2 and an elongation percentage of 46 to 55%, more preferably a tensile strength of 100 to 105 kgf / mm 2, a yield strength of 45 to 49 kgf / mm 2 and an elongation percentage of 47 to 52%.
또한, 상기 시효경화를 수행하기 전의 볼트 소재는KS B 1003 방법에 의거하여 측정시 단면수축률(Reduction of area) 65 ~ 75% 및 KS B 1003 방법에 의거하여 측정시 경도(hardness) 35 ~ 45 HRC를 만족할 수 있으며, 바람직하게는 단면수축률 67 ~ 72% 및 경도 36 ~ 44 HRC를 만족할 수 있고, 더욱 바람직하게는 단면수축률 68 ~ 72% 및 경도 38 ~ 44 HRC를 만족할 수 있다.
The bolt material before aging hardening has a hardness of 35 to 45 HRC when measured according to KS B 1003 method and a hardness of 35 to 45 HRC when measured according to the KS B 1003 method, , Preferably a cross-sectional shrinkage ratio of 67 to 72% and a hardness of 36 to 44 HRC, more preferably a cross-sectional shrinkage ratio of 68 to 72% and a hardness of 38 to 44 HRC.
그리고, 본 발명에 있어서 상기 시효경화시키는 단계는 냉간단조된 볼트를 700 ~ 750℃ 하에서, 바람직하게는 710 ~ 730℃ 하에서 15 ~ 17시간 동안 진공열처리를 수행할 수 있으며, 이때, 진공열처리 온도가 700℃ 미만이면 원하는 경도 스펙을 만족하는 볼트를 얻을 수 없을 수 있고, 온도가 750℃를 초과하면 볼트의 인장강도가 낮은 문제가 있을 수 있다. 그리고, 진공열처리 시간은 상기 온도 범위에서 원하는 물성 스펙을 만족시키는 볼트를 제조하기 위한 적정 시간인 것이다.According to the present invention, the aging and curing may be performed by vacuum-annealing the cold-forged bolt at 700 to 750 ° C, preferably at 710 to 730 ° C for 15 to 17 hours. At this time, If it is less than 700 ° C, a bolt satisfying the desired hardness specification may not be obtained. If the temperature exceeds 750 ° C, there may be a problem that the tensile strength of the bolt is low. The vacuum heat treatment time is a suitable time for manufacturing the bolt satisfying the desired physical property specification in the temperature range.
또한, 상기 시효경화시키는 단계는 진공도 110-4 ~ 510-3 torr, 바람직하게는 510-4 ~ 510-3 torr 하에서 수행할 수 있으며, 이때, 진동도가 110-4 torr 미만이면 이러한 조건을 만족시키기 위한 설비공정비가 너무 급격하게 증가하는 문제가 있을 수 있고, 진공도가 510-3 torr를 초과하면 원하는 물성 스펙을 갖는 볼트를 제조할 수 없을 수 있으므로 상기 범위 내에서 수행하는 것이 좋다. 또한, 상기 시효경화시키는 단계는 산소 1 ppm 이하 및 유기불순물 1.5 ppm 이하의 조건에서 수행하는 것이 바람직하다.Further, the step of age hardening may be carried out under vacuum of 110 torr -3 -4 ~ 510, preferably 510 ~ 510 -4 -3 torr, At this time, if the oscillation degree is less than 110 -4 torr satisfy this condition there may be a problem that the process equipment ratio increases too steeply for, when the degree of vacuum is more than 510 -3 torr may not be able to produce a bolt with the desired physical properties of the specification may be carried out within this range. In addition, it is preferable that the age-hardening step is performed under the condition of not more than 1 ppm of oxygen and not more than 1.5 ppm of organic impurities.
또한, 시효경화시키는 단계는 진공열처리한 볼트를 상온에서 서서히 냉각시킬수도 있으며, 또는 공랭(air cooling)시키는 공정을 더 포함할 수 있다.In addition, the age hardening step may further include a step of slowly cooling the vacuum heat-treated bolt at room temperature, or air cooling the bolt.
이와 같은 조건에서 시효경화시킨 볼트는 KS B 1003 방법에 의거하여 측정시, 경도가 35 ~ 42 HRC이고, KS B 1003 방법에 의거하여 측정시, 인장강도가 165 ~ 225 kgf/㎟을 만족할 수 있으며, 바람직하게는 경도 36 ~ 41 HRC 및 인장강도 165 ~ 220 kgf/㎟을 갖을 수 있다.Under these conditions, the hardened bolt has a hardness of 35 to 42 HRC when measured according to the KS B 1003 method, and a tensile strength of 165 to 225 kgf / mm 2 when measured according to the KS B 1003 method , Preferably a hardness of 36 to 41 HRC and a tensile strength of 165 to 220 kgf / mm < 2 >.
또한, 시효경화시킨 볼트는 KS B 1003 방법에 의거하여 측정시, 항복강도 80 ~ 95 kgf/㎟, KS B 1003 방법에 의거하여 측정시 신장율 140 ~ 160%이며, KS B 1003 방법에 의거하여 측정시 단면수축률 15 ~ 30%을 만족할 수 있으며, 바람직하게는 항복강도 82 ~ 90 kgf/㎟, 신장율 142 ~ 155% 및 단면수축률 17 ~ 25%을 갖을 수 있다.
In addition, the age hardened bolt has a yield strength of 80 to 95 kgf / mm 2 when measured according to the KS B 1003 method, an elongation of 140 to 160% when measured according to the KS B 1003 method, and a measurement based on the KS B 1003 method The shrinkage ratio at the time of 15 to 30% can be satisfied, and preferably the yield strength is 82 to 90 kgf / mm 2, the elongation is 142 to 155%, and the shrinkage ratio is 17 to 25%.
본 발명에 있어서, 시효경화공정을 수행한 후, 나사전조가공하는 단계를 수행할 수 있으며, 나사전조가공은 당업계에서 사용하는 일반적인 방법을 사용하여 시효경화공정을 수행한 볼트를 나사와 결합시킬 수 있도록 볼트 홈을 형성시킬 수 있다.In the present invention, after the aging hardening process is performed, a screw rolling process may be performed. In the screw rolling process, a screw having been subjected to the aging hardening process using a general method used in the art may be screwed A bolt groove can be formed.
그리고, 나사전조가공시킨 볼트의 표면을 다듬기 위해 부동태 처리를 할 수 있으며, 부동태 처리는 당업계에서 사용하는 일반적인 방법을 사용할 수 있으며, 바람직하게는 마찰연마법을 수행하여 할 수 있다.In addition, passivation treatment can be performed to trim the surface of the bolt threaded screw, and passivation treatment can be performed by a general method used in the related art. Preferably, friction welding is performed.
또한, 부동태 처리한 볼트를 광택을 주고, 이물질을 제거하기 위해 화학연마액으로 화학연마처리하는 단계를 수행할 수 있으며, 이때, 화학연마액의 예를 들면, 인산 100 중량부에 대하여, 황산 3 ~ 20 중량부, 초산 5 ~ 15 중량부 및 기타 첨가제를 포함하는 화학연마액을 사용할 수 있다.
In addition, a step of chemically polishing the passivated bolt with a chemical polishing solution to polish and remove foreign substances can be carried out. At this time, for example, in the chemical polishing solution, sulfuric acid 3 To 20 parts by weight, acetic acid 5 to 15 parts by weight, and other additives may be used.
이와 같은 방법을 통해서 AMS 5731 L 과 같은 인공위성용 볼트 규격을 만족하는 고스펙의 우주선용 볼트를 제공할 수 있으며, 본 발명의 제법으로 제조한 볼트는 우주선뿐만 아니라, 이와 유사한 환경 등에서 사용되어 고스펙을 요구하는 장치, 예를 들면, 심해용 잠수함, 선박, 비행기 등에도 사용할 수 있다.
In this way, it is possible to provide a high-spec space bolt satisfying the artificial bolt standard such as AMS 5731 L, and the bolt manufactured by the method of the present invention can be used not only in spacecraft but also in similar environments, , Such as deep sea submarines, ships, airplanes, etc.
이하에서는 본 발명을 실시예에 의거하여 더욱 자세하게 설명을 한다. 그러나, 본 발명의 권리범위가 하기 실시예에 의해 한정되는 것은 아니다.
Hereinafter, the present invention will be described in more detail with reference to examples. However, the scope of the present invention is not limited by the following examples.
[실시예][Example]
준비예 1Preparation Example 1
하기 표 1의 화학적 성분을 갖는 볼트용 소재를 준비한 후, 이를 냉간단조시켰으며, 냉간단조공정을 찍은 사진을 도 1에 나타내었다.A bolt material having the chemical composition shown in the following Table 1 was prepared, then cold-forged and a cold forging process was shown in FIG.
다음으로 냉간단조시킨 볼트용 소재를 도 2와 같이 볼트크기로 절단하였고, 절단시킨 볼트용 소재의 물성을 하기 표 2에 나타내었다.
Next, the cold-forged bolt material was cut to a bolt size as shown in FIG. 2, and physical properties of the material for the bolt cut are shown in Table 2 below.
(중량%)content
(weight%)
Co=0.18
N=0.36
Al=0.14
Ti=2.23
Pb=0.0001 이하
Bi=0.2ppm 이하
B=0.007
Zr=0.005 이하Cu = 0.16
Co = 0.18
N = 0.36
Al = 0.14
Ti = 2.23
Pb = 0.0001 or less
Bi = 0.2 ppm or less
B = 0.007
Zr = 0.005 or less
(kgf/㎟)The tensile strength
(kgf / mm2)
(kgf/㎟)Yield strength
(kgf / mm2)
(%)Elongation rate
(%)
(%)Section shrinkage
(%)
(HRC)Hardness
(HRC)
실시예 1Example 1
상기 준비예 1에서 제조한 볼트용 소재를 진공열처리로에 투입한 후, 질소 가스, 720℃, 110-3 torr, 산소 1 ppm 이하 및 유기불순물 1.5 ppm 이하의 조건 하에서 16시간 동안 진공열처리하여, 시효경화를 수행하였다.The material for the bolt prepared in Preparation Example 1 was placed in a vacuum heat treatment furnace and subjected to a vacuum heat treatment for 16 hours under the conditions of nitrogen gas, 720 DEG C, 110-3 torr, oxygen of 1 ppm or less and organic impurities of 1.5 ppm or less, Aging hardening was performed.
다음으로, 진공열처리한 볼트를 공기냉각(공랭, air cooling)시켰다.Next, the vacuum heat treated bolts were air cooled (air cooling).
다음으로, 나사전조가공을 통해 볼트 홈을 형성시킨 후, 마찰연마시켜서 부동태처리를 하였으며, 부동태 처리한 우주선용 볼트의 사진을 도 3 및 도 4에 나타내었다.
Next, bolt grooves are formed through thread rolling, and then passivation is performed by friction grinding. Figs. 3 and 4 show photographs of passive bolts for spacecrafts.
실시예 2Example 2
상기 실시예 1과 동일한 준비예 1에서 제조한 볼트용 소재를 사용하여 시효경화를 수행하여 동일한 방법으로 볼트를 제조하되, 공랭시키지 않고, 상온(24 ~ 30℃)에서 서서히 냉각시킨 후, 실시예 1과 동일한 방법으로 나사전조가공 및 부동태 처리하여 우주선용 볼트를 제조하였다.
The bolts were produced in the same manner as in Example 1 except that the bolts were produced by the same method as in Example 1 except that the bolts were gradually cooled at room temperature (24 to 30 ° C) without air cooling, 1, the bolts for spacecraft were manufactured by thread rolling and passivation.
실시예 3Example 3
상기 실시예 1과 동일한 준비예 1에서 제조한 볼트용 소재를 사용하여 시효경화를 수행하여 동일한 방법으로 볼트를 제조하되, 진공열처리 온도를 730℃ 하에서 17시간 동안 진공열처리하여, 시효경화를 수행한 것을 제외하고는 동일한 방법으로 우주선용 볼트를 제조하였다.
A bolt was produced in the same manner by performing age hardening using the material for a bolt manufactured in Preparation Example 1, which was the same as Example 1, and subjected to vacuum heat treatment at 730 캜 for 17 hours to perform aging hardening A spacecraft bolt was manufactured in the same way except that.
비교예 1Comparative Example 1
상기 준비예 1에서 제조한 볼트용 소재를 열처리로에 투입한 후, 질소 가스, 980℃ 하에서 1 시간 동안 용체화 처리를 수행하였다.The material for bolts prepared in Preparation Example 1 was put into a heat treatment furnace, and then a solution treatment was performed for 1 hour at 980 占 폚 with nitrogen gas.
다음으로, 용체화 처리한 볼트용 소재를 질소 가스, 720℃, 110-3 torr, 산소 1 ppm 이하 및 유기불순물 1.5 ppm 이하의 조건 하에서 16시간 동안 시효경화를 수행하였다.Next, aging curing was performed for 16 hours under the conditions of nitrogen gas, 720 占 폚, 110-3 torr, oxygen of 1 ppm or less and organic impurities of 1.5 ppm or less.
다음으로, 진공열처리한 볼트를 공기냉각(공랭, air cooling)시켰다.Next, the vacuum heat treated bolts were air cooled (air cooling).
다음으로, 실시예 1과 동일한 방법으로 나사전조가공 및 부동태 처리하여 우주선용 볼트를 제조하였다.
Next, a bolt for spacecraft was manufactured by screw rolling and passivating in the same manner as in Example 1.
비교예 2Comparative Example 2
상기 준비예 1에서 제조한 볼트용 소재를 열처리로에 투입한 후, 질소 가스, 900℃ 하에서 2 시간 동안 용체화 처리를 수행하였다.The material for the bolt prepared in Preparation Example 1 was put into a heat treatment furnace and then subjected to a solution treatment at 900 DEG C for 2 hours.
다음으로, 용체화 처리한 볼트용 소재를 질소 가스, 720℃, 110-3 torr, 산소 1 ppm 이하 및 유기불순물 1.5 ppm 이하의 조건 하에서 16시간 동안 시효경화를 수행하였다.Next, aging curing was performed for 16 hours under the conditions of nitrogen gas, 720 占 폚, 110-3 torr, oxygen of 1 ppm or less and organic impurities of 1.5 ppm or less.
다음으로, 실시예 1과 동일한 방법으로 나사전조가공 및 부동태 처리하여 우주선용 볼트를 제조하였다.
Next, a bolt for spacecraft was manufactured by screw rolling and passivating in the same manner as in Example 1.
비교예 3Comparative Example 3
상기 실시예 1과 동일한 준비예 1에서 제조한 볼트용 소재를 사용하여 시효경화를 수행하여 동일한 방법으로 볼트를 제조하되, 진공열처리 온도를 690℃ 하에서 16시간 동안 진공열처리하여, 시효경화를 수행한 것을 제외하고는 동일한 방법으로 우주선용 볼트를 제조하였다.
A bolt was manufactured in the same manner as in Example 1 by performing aging and curing using the bolt material prepared in Preparation Example 1, and vacuum heat treatment was performed at 690 캜 for 16 hours to perform aging hardening A spacecraft bolt was manufactured in the same way except that.
비교예 4Comparative Example 4
상기 실시예 1과 동일한 준비예 1에서 제조한 볼트용 소재를 사용하여 시효경화를 수행하여 동일한 방법으로 볼트를 제조하되, 진공열처리 온도를 770℃ 하에서 16시간 동안 진공열처리하여, 시효경화를 수행한 것을 제외하고는 동일한 방법으로 우주선용 볼트를 제조하였다.
A bolt was produced in the same manner as in Example 1 by performing aging hardening using the material for bolt prepared in Preparation Example 1. The vacuum heat treatment was conducted at a vacuum heat treatment temperature of 770 DEG C for 16 hours to effect aging hardening A spacecraft bolt was manufactured in the same way except that.
실험예 1 : 볼트의 물성 측정Experimental Example 1: Measurement of physical properties of bolts
상기 실시예 및 비교예에서 제조한 볼트의 경도, 인장강도, 항복강도, 신장율, 단면수축률을 각각 KS B 1003에 의거하여 측정하였으며, 그 결과를 하기 표 3에 나타내었다. AMS 5731L에 따른 인공위성용 볼트의 스펙(spec)은 경도 HRC 33 ~ 42, 인장강도 160 kgf/㎟ 이상, 항복강도 80 kgf/㎟ 이상, 신장율 140% 이상, 단면수축률 40% 미만을 만족해야 한다.
The hardness, tensile strength, yield strength, elongation, and cross-sectional shrinkage of the bolts prepared in the above Examples and Comparative Examples were measured according to KS B 1003, respectively, and the results are shown in Table 3 below. Specs of satellite bolts according to AMS 5731L should satisfy hardness HRC 33 ~ 42, tensile strength 160 kgf / ㎟ or higher, yield strength 80 kgf / ㎟, elongation more than 140% and less than 40% section shrinkage.
(kgf/㎟)The tensile strength
(kgf / mm2)
(kgf/㎟)Yield strength
(kgf / mm2)
(%)Elongation rate
(%)
(%)Section shrinkage
(%)
(HRC)Hardness
(HRC)
상기 표 3의 볼트의 물성 측정 결과를 살펴보면, 실시예 1 ~ 3의 경우, 인공위성과 같은 우주선용 볼트 요구되는 인장강도, 항복강도, 신장율, 단면수축률 및 경도의 스펙을 만족하는 것을 확인할 수 있었다.As a result of the measurement of the physical properties of the bolts in Table 3, it was confirmed that in Examples 1 to 3, the specifications of tensile strength, yield strength, elongation, shrinkage and hardness required for spacecraft bolts such as artificial satellites were satisfied.
그러나, 비교예 1 ~ 2와 같이, 용체화 공정을 수행하는 경우, 다른 물성은 우수하나 경도가 좋지 않은 문제가 있었다. 그리고, 시효경화처리시, 700℃ 이하에서 수행한 비교예 3의 경우, 인장강도 등의 물성은 우수하나, 경도가 떨어지는 문제가 있었으며, 시효경화처리시, 750℃ 초과하는 온도에서 수행한 비교예 4의 경우, 경도 및 다른 물성은 우수하나, 인장강도가 저조한 문제가 있었다.
However, as in the case of Comparative Examples 1 and 2, there was a problem in that, when the solution process was carried out, the other properties were excellent but the hardness was poor. Comparative Example 3 performed at 700 ° C or lower during aging hardening treatment had excellent properties such as tensile strength but was inferior in hardness. In the aging hardening treatment, Comparative Example 3 which was performed at a temperature exceeding 750 ° C 4 had excellent hardness and other physical properties but had a problem of low tensile strength.
상기 실시예 및 실험예를 통하여 본 발명이 제시하는 볼트 제조방법을 통해서 용체화 열처리 공정을 수행하지 않으면서도 인공위성과 같은 우주선용 볼트로서 요구되는 물성을 만족하는 볼트를 제공할 수 있음을 확인할 수 있었으며, 본 발명의 제조방법을 통해 경제성, 상업성이 우수한 첨단부품소재인 우주선용 볼트를 제공할 수 있음을 확인할 수 있었다. 이러한 본 발명의 볼트는 우주선 뿐만 아니라, 심해용 잠수함, 비행기 등 혹독한 환경에서 운행되는 기계 등에도 응용하여 사용할 수 있을 것으로 기대된다.It is possible to provide a bolt satisfying the physical properties required for spacecraft bolts such as artificial satellites without performing the solution heat treatment process through the bolt manufacturing method of the present invention through the embodiments and the experimental examples , It can be confirmed that a bolt for spacecraft, which is an advanced part material excellent in economy and commerciality, can be provided through the manufacturing method of the present invention. Such a bolt of the present invention is expected to be applied not only to spacecraft but also to machines operating in harsh environments such as deep sea submarines and airplanes.
Claims (13)
냉간단조된 볼트용 소재를 700℃ ~ 750℃ 하에서 15 ~ 17시간 동안 진공열처리를 수행하여 시효경화시킨 볼트를 제조하는 단계;
시효경화시킨 볼트를 나사전조가공하는 단계; 및
나사전조가공한 볼트를 부동태처리하는 단계;를 포함하는 공정을 수행하며,
시효경화 이전에 용체화 처리를 수행하지 않는 것을 특징으로 하는 우주선용 볼트를 제조하는 방법.
Wherein the molybdenum is at least one selected from the group consisting of carbon 0.035 to 0.045 wt% manganese 1.74 to 1.76 wt% silicon 0.19 to 0.21 wt% sulfur 0.002 to 0.004 wt% phosphorus 0.015 to 0.017 wt% nickel 24.4 to 24.7 wt% chromium 14.7 to 14.9 wt% Wherein the aluminum alloy comprises at least one of the following elements: 1.23 to 1.28 wt%, copper 0.15 to 0.17 wt%, cobalt 0.17 to 0.19 wt%, nitrogen 0.34 to 0.38 wt%, aluminum 0.12 to 0.16 wt%, titanium 2.20 to 2.30 wt%, boron 0.004 to 0.010 wt% By weight of the steel material for a bolt, wherein the steel material for the bolt is cold-forged;
Subjecting the cold forged bolt material to a vacuum heat treatment at 700 ° C to 750 ° C for 15 to 17 hours to produce an aged hardened bolt;
Screw aging the aged bolt; And
And passivating the threaded bolt,
Wherein the solution treatment is not performed prior to age hardening.
The method of manufacturing a spacecraft bolt according to claim 1, further comprising chemically polishing the passivated bolt with a chemical polishing solution at 100 to 140 占 폚.
The method according to claim 1, wherein in the age hardening step, the bolt before aging hardening has a tensile strength of 95 to 120 kgf / mm < 2 > when measured according to the KS B 1003 method, A yield strength of 40 to 55 kgf / mm 2 and an elongation of 45 to 60% as measured according to the KS B 1003 method.
5. The method of claim 4, wherein in the cold forging step, the bolt before aging is hardened has a reduction in area of 65 to 75% when measured according to the KS B 1003 method and a hardness wherein the hardness is 35 to 45 HRC.
7. The method according to claim 6, wherein the vacuum heat treatment of the aging curing step is carried out under 1 ppm oxygen, 1.5 ppm organic impurities and under a nitrogen gas.
2. The method of claim 1, wherein aging curing further comprises air cooling the vacuum heat treated bolts.
The aged bolt according to claim 1, wherein the aged hardened bolt has a hardness of 35 to 42 HRC and a tensile strength of 165 to 225 kgf / mm 2 when measured according to the KS B 1003 method Wherein the bolt is made of a metal.
The method of claim 1, wherein the age-hardened bolt has a yield strength of 80 to 95 kgf / mm 2 when measured according to the KS B 1003 method, an elongation of 140 to 160% as measured by the KS B 1003 method, and a KS B 1003 method Wherein the cross-sectional shrinkage of the bolt is 15 to 30% when measured according to the following formula.
The method of manufacturing a spacecraft bolt according to claim 1, wherein the step of passivating is performed by friction joining.
The method of manufacturing a spacecraft bolt according to claim 2, wherein the chemical polishing solution comprises 3 to 20 parts by weight of sulfuric acid and 5 to 15 parts by weight of acetic acid per 100 parts by weight of phosphoric acid .
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| KR20190071313A (en) | 2017-12-14 | 2019-06-24 | 정기선 | Hard cast alloy bolts and their manufacturing methodsod |
| KR102102366B1 (en) * | 2019-12-13 | 2020-04-20 | 김창재 | Reinforcement structure using steel plate with guide anchor for controlling distance |
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| KR20080063137A (en) * | 2006-12-28 | 2008-07-03 | 가부시키가이샤 고베 세이코쇼 | Steel for high-speed cold working and method for production thereof, and part formed by high-speed cold working and method for production thereof |
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| JPH10110248A (en) * | 1996-10-03 | 1998-04-28 | Hitachi Metals Ltd | High hardness martensitic stainless steel excellent in pitting corrosion resistance |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR20190071313A (en) | 2017-12-14 | 2019-06-24 | 정기선 | Hard cast alloy bolts and their manufacturing methodsod |
| KR102102366B1 (en) * | 2019-12-13 | 2020-04-20 | 김창재 | Reinforcement structure using steel plate with guide anchor for controlling distance |
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