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1. 发明授权

KR101549952B1 추력 노즐용 익시트 콘 제조방법 有权
标题翻译：推进喷嘴单元出口锥体的制造方法
公开(公告)号：KR101549952B1
公开(公告)日：2015-09-03
申请号：KR1020130135671
申请日：2013-11-08
申请人： 국방과학연구소
发明人： 김연철 , 이형식 , 구형회
IPC分类号： C04B41/00 , C04B35/56 , F02K1/00
摘要： 본발명의추력노즐용익시트콘 제조방법에서는탄소계, 실리콘카바이드계섬유(직물)를기본으로하여직물프리폼(10,knit preform), 테이프프리폼(20,Tape preform), 인볼트레이업프리폼(30,Involute layup preform), 필라멘트프리폼(Filament preform)을다양하게제조하고, 이러한다양한프리폼(preform)을고온내열수지함침, 탄화, 고밀도화및 내산화처리공정을통하여삭마저항성과 열구조성능이우수한박막형고성능확대부내열부품인익시트콘(5)으로제조됨으로써중량감소가성능에큰 영향을끼치는고성능유도무기부품에적용이가능한특징을갖는다.

2. 发明授权

KR100417161B1 탄소직물로 이루어진 Ｃ/ＳｉＣ 복합재료의 제조방법 有权
标题翻译： 탄소직물로이루어진C / SiC복합재료의제조방법
公开(公告)号：KR100417161B1
公开(公告)日：2004-02-05
申请号：KR1020010006790
申请日：2001-02-12
申请人： 국방과학연구소
发明人： 김연철 , 원용구 , 이형식 , 임광현 , 신동혁
IPC分类号： C04B35/56 , C04B41/52 , B32B18/00
CPC分类号： C04B41/52 , C04B35/573 , C04B35/806 , C04B41/5059 , C04B2235/428 , C04B2235/48 , C04B2235/5256 , C04B2235/60 , C04B2235/616 , C04B2235/77 , C04B41/4529 , C04B41/4556 , C04B41/4539 , C04B41/5064
摘要： A method for manufacturing carbon/silicon-carbide composite by a "One-shot' process including carbonization, heat processing, infiltration, and forming an anti-oxidation layer on surface is provided through the steps of: 1) hardening a stacked carbon/phenolic preform; 2) carbonization and heat processing the preform until the temperature reaches at 2300° C.; 3) infiltrating and sintering the liquid metal silicon within the temperature of 1400~1800° C.; and 4) inducting a compound including SiO2to gas phase and heat processing it while forming an anti-oxidation layer on the surface within temperature range of 2000° C.~2700° C. (desirably, in the range of higher than 2300° C., and more desirably, at the temperature near 2500° C.). Herein, the carbonization, heat processing, and ultra-high heat processing might be performed at the same time in the step 2) and the step 4) might not be performed.
摘要翻译：通过包括碳化，热处理，渗透和在表面上形成抗氧化层的“一步法”工艺来制造碳/碳化硅复合材料的方法通过以下步骤提供：1）将堆叠的碳/ 酚醛预制件; 2）碳化和热处理预制件直至温度达到2300℃; C。; 3）在1400〜1800℃温度范围内渗透并烧结液态金属硅。 C。; 和4）将包含SiO2的化合物引入气相并对其进行热处理，同时在2000℃的温度范围内在表面上形成抗氧化层。 C.〜2700℃下与; （希望在高于2300℃的范围内，更理想的是在2500℃附近的温度下）。此处，可能在步骤2）中同时进行碳化，热处理和超高温处理，并且可能不执行步骤4）。

3. 发明公开

KR1020150053567A 추력 노즐용 익시트 콘 제조방법 有权
标题翻译：推进喷嘴单元出口锥度的制造方法
公开(公告)号：KR1020150053567A
公开(公告)日：2015-05-18
申请号：KR1020130135671
申请日：2013-11-08
申请人： 국방과학연구소
发明人： 김연철 , 이형식 , 구형회
IPC分类号： C04B41/00 , C04B35/56 , F02K1/00
CPC分类号： C04B41/00 , C04B35/56 , F02K1/00
摘要： 본발명의추력노즐용익시트콘 제조방법에서는탄소계, 실리콘카바이드계섬유(직물)를기본으로하여직물프리폼(10,knit preform), 테이프프리폼(20,Tape preform), 인볼트레이업프리폼(30,Involute layup preform), 필라멘트프리폼(Filament preform)을다양하게제조하고, 이러한다양한프리폼(preform)을고온내열수지함침, 탄화, 고밀도화및 내산화처리공정을통하여삭마저항성과 열구조성능이우수한박막형고성능확대부내열부품인익시트콘(5)으로제조됨으로써중량감소가성능에큰 영향을끼치는고성능유도무기부품에적용이가능한특징을갖는다.
摘要翻译：本发明的推进喷嘴出口锥体的制造方法可以通过以碳基和碳化硅为基础的织物作为基材制造各种针织预成型件（10），预成型件（20），渐开线上料预成型件（30）和长丝预制件; 以及出口锥体（5），其是通过高温耐热树脂浸渍，碳化，高致密化和抗氧化处理，具有薄膜形状的具有优异热结构的高性能膨胀部分耐热组分各种预成型件; 因此，本发明可以应用于由于重量损失而受到很大影响的高性能导向武器部件。

4. 发明授权

KR100832734B1 3자유도 회전 운동체 구동장치 有权
标题翻译：用3度自由角运动的装置
公开(公告)号：KR100832734B1
公开(公告)日：2008-05-27
申请号：KR1020070020607
申请日：2007-02-28
申请人： 국방과학연구소
发明人： 조성진 , 김을곤 , 이형식
IPC分类号： B64C15/00
CPC分类号： F02K9/84 , B64G1/401
摘要： An apparatus for driving a rotary moving body with 3 degrees of freedom is provided to limit rolling of the moving body connected to a fixing part to perform inclined movement with 2 degrees of freedom. An apparatus for driving a rotary moving body with 3 degrees of freedom includes a fixing part, a moving body(30), a pitch drive unit(40), a yaw drive unit(50), a drive source, a control valve, a first sensor, a second sensor, and a controller. The moving part is connected to the fixing part by a ball socket joint(20). The pitch drive unit includes a pitch cylinder(41), a pitch piston(42), and a pitch connecting rod(46). The pitch cylinder is connected to the drive source. The pitch piston is reciprocally installed at the pitch cylinder in a yaw axis direction. The position of the pitch piston is detected by the first sensor.
摘要翻译：提供一种用于驱动具有3个自由度的旋转移动体的装置，以限制连接到固定部分的移动体的滚动，以进行具有2个自由度的倾斜运动。用于驱动具有3个自由度的旋转运动体的装置包括固定部，移动体（30），俯仰驱动单元（40），偏航驱动单元（50），驱动源，控制阀，第一传感器，第二传感器和控制器。移动部分通过球窝接头（20）连接到固定部分。俯仰驱动单元包括俯仰缸（41），俯仰活塞（42）和俯仰杆（46）。变桨缸连接到驱动源。俯仰活塞在偏转轴方向上以俯仰柱体往复地安装。俯仰活塞的位置由第一传感器检测。

5. 发明公开

KR1020020066547A 탄소직물로 이루어진 Ｃ/ＳｉＣ 복합재료의 제조방법 有权
标题翻译：生产包含碳纤维的C / SIC复合材料
公开(公告)号：KR1020020066547A
公开(公告)日：2002-08-19
申请号：KR1020010006790
申请日：2001-02-12
申请人： 국방과학연구소
发明人： 김연철 , 원용구 , 이형식 , 임광현 , 신동혁
IPC分类号： C04B35/56 , C04B41/52 , B32B18/00
CPC分类号： C04B41/52 , C04B35/573 , C04B35/806 , C04B41/5059 , C04B2235/428 , C04B2235/48 , C04B2235/5256 , C04B2235/60 , C04B2235/616 , C04B2235/77 , C04B41/4529 , C04B41/4556 , C04B41/4539 , C04B41/5064
摘要： PURPOSE: A production method of C/SiC composite materials comprising carbon fibers is provided to decrease manufacturing time and costs greatly by one-shot process including carbonization, thermal treatment, impregnation and formation of oxidation resistant layer unlike conventional chemical vapor infiltration process. CONSTITUTION: The C/SiC composite materials with good heat resistance for missile nozzles, supersonic flight engines, high temperature valves, etc. are produced by the following steps of: (i) layering carbon/phenolic preforms and hardening, wherein the preform is one of various preforms prepared by press molding, filament winding, sewing, and involute method; (ii) carbonizing phenolic resin, and heating to 2300deg.C or lower; (iii) impregnating with liquid metal silicon and sintering between 1400 and 1800deg.C, and optionally coating the sintered sample with BN mixture comprising 70-80% of BN, 10-20% of acetone, and 0-10% of water; (iv) heating to 2000-2700deg.C to form an oxidation resistant layer on the surface of preform caused by vaporization of Si-contained compound. Also, the C/SiC composite materials are produced by performing carbonization, thermal treatment and super-high temperature thermal treatment at the same time, and excluding step (iv). The hardened sample from step (i) is processed by making holes with 0.5-1.5mm diameter at 5-20mm intervals, where the holes are used to discharge decomposed gas from the step (ii).
摘要翻译：目的：提供一种包含碳纤维的C / SiC复合材料的生产方法，通过与常规化学气相渗透方法不同的碳化，热处理，浸渍和抗氧化层的形成，通过一步法大大减少制造时间和成本。构成：通过以下步骤制备导弹喷嘴，超音速飞行发动机，高温阀等具有良好耐热性的C / SiC复合材料：（i）分层碳/酚醛预成型件和硬化，其中预制件为一通过压模，丝缠绕，缝合和渐开线方法制备的各种预成型件; （ii）碳化酚醛树脂，加热至2300℃以下; （iii）用液态金属硅浸渍并烧结在1400至1800℃之间，并且任选地用包含70-80％BN，10-20％丙酮和0-10％水的BN混合物涂覆烧结样品; （iv）加热至2000-2700℃，以由含Si化合物蒸发而在预成型体表面形成抗氧化层。此外，C / SiC复合材料通过同时进行碳化，热处理和超高温热处理而制造，并且不包括步骤（iv）。步骤（i）的硬化样品通过以5-20mm的间隔制造具有0.5-1.5mm直径的孔，其中用于从步骤（ii）排出分解气体。

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