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公开(公告)号：KR1020110027469A
公开(公告)日：2011-03-16
申请号：KR1020090085574
申请日：2009-09-10
Applicant: 국방과학연구소
CPC classification number: G01N3/08 , G01N2203/0017 , G01N2203/0226 , G01N2203/0266
Abstract: PURPOSE: A tensile testing device and a tensile testing method are provided to enable accurate measurement, since an expansion tube is placed on the inner circumference of the cylindrical specimen. CONSTITUTION: A tensile testing device comprises an expansion tube(110), a ring-type support member(120), an upper support member(130), and a lower support member(140). The expansion tube is expanded by the increment of the internal pressure, so load is applied on a cylindrical specimen(200) in a columnar direction. The ring-type support member supports the inner circumference of the expansion tube to order to restrict the inward expansion of the expansion tube. The upper support member supports the top of the expansion tube in order to restrict the upward expansion of the expansion tube. The lower support member supports the lower part of the expansion tube in order to restrict the downward expansion of the expansion tube.
Abstract translation: 目的：提供拉伸试验装置和拉伸试验方法，以便能够进行精确的测量，因为膨胀管放置在圆柱形试样的内圆周上。 构成：拉伸试验装置包括膨胀管（110），环型支撑构件（120），上支撑构件（130）和下支撑构件（140）。 膨胀管通过内部压力的增加而膨胀，因此在柱状方向上将负载施加在圆柱形试样（200）上。 环形支撑构件支撑膨胀管的内周，以限制膨胀管的向内膨胀。 上支撑构件支撑膨胀管的顶部以限制膨胀管的向上膨胀。 下支撑构件支撑膨胀管的下部以限制膨胀管的向下膨胀。
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公开(公告)号：KR100785376B1
公开(公告)日：2007-12-18
申请号：KR1020060115125
申请日：2006-11-21
Applicant: 국방과학연구소
CPC classification number: G01N3/18 , G01N3/02 , G01N2203/0023 , G01N2203/0039 , G01N2203/0226
Abstract: An apparatus for a high temperature bending test of composite material structure using a load transfer path and a direction switch is provided to exactly measure the high temperature bending character of a composite material structure with separating the movement of a zero point by a temperature rising. An apparatus for a high temperature bending test of composite material structure using a load transfer path and a direction switch includes a weight holder(09), a winch(10), a supporting wire rope, a roller pin(07), a load transmitting wire rope(12), and a beam structure. The winch has a structure which is able to wind a wire, and is installed at the upper of an oven above the vertical direction of the weight holder. The supporting wire rope is connected with the winch and the weight holder. The roller pin has a structure which is able to wind a wire and is vertically installed at the upper of the weight holder. The lower end of the load transmitting wire rope is vertically extended by being connected to the weight holder and an upper end of the load transmitting wire is extended in horizontal by changing the direction thereof due to the roller pin to be connected to a structure for test. The beam structure has a flange(01) vertically electing and fixing the lower portion of the structure and a roller holder(06) fixing the roller pin.
Abstract translation: 提供了一种使用负载传递路径和方向开关进行复合材料结构的高温弯曲试验的装置，以精确地测量复合材料结构的高温弯曲特性，将零点的移动与温度升高分开。 一种用于使用负载传递路径和方向开关的复合材料结构的高温弯曲试验的装置包括：重物架（09），绞盘（10），支撑钢丝绳，滚针（07），载荷传递 钢丝绳（12）和梁结构。 绞车具有能够缠绕线的结构，并且安装在比重锤架的垂直方向上方的烤箱上方。 支撑钢丝绳与绞盘和重物架连接。 滚针具有能够缠绕线并垂直地安装在重物架的上部的结构。 负载传送钢丝绳的下端通过连接到重量保持器而垂直延伸，并且负载传输线的上端通过改变由于滚子销引起的连接到测试结构的方向而在水平方向上延伸 。 梁结构具有垂直选择和固定结构的下部的凸缘（01）和固定辊销的辊保持器（06）。
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公开(公告)号：KR101428575B1
公开(公告)日：2014-08-11
申请号：KR1020130100098
申请日：2013-08-23
Applicant: 국방과학연구소
Abstract: Provided are a composite combustion pipe with an integrally-shaped detachable dome and a method of manufacturing the same. The present invention relates to a combustion pipe for use in a solid rocket propulsion engine, including a front dome unit mounted with a tubular metal boss on a central axis; a cylindrical unit extending from the front dome unit coaxially with the metal boss; and a front tubular skirt inserted into the front dome unit to coincide with the cylindrical unit. The front dome unit and the cylindrical unit are formed by stacking a rubber layer and a carbon fiber layer, and different carbon fiber layers are coated on the front dome unit and the cylindrical unit. Since a primary layer to form the front dome unit is removed from the cylindrical unit to make the thickness of the cylindrical unit thin, the inner space of the combustion pipe is increased, and the amount of a propellant is increased.
Abstract translation: 提供一种具有整体形状的可拆卸圆顶的复合燃烧管及其制造方法。 本发明涉及一种用于固体火箭推进发动机的燃烧管，其包括在中心轴线处安装有管状金属凸台的前圆顶单元; 圆柱形单元，其与前述圆顶单元从金属凸台同轴地延伸; 以及插入到前圆顶单元中以与圆柱形单元重合的前管状裙部。 前圆顶单元和圆柱形单元通过堆叠橡胶层和碳纤维层形成，并且在前圆顶单元和圆柱形单元上涂覆不同的碳纤维层。 由于从圆柱形单元移除形成前圆顶单元的初级层以使圆柱形单元的厚度变薄，所以燃烧管的内部空间增加，并且推进剂的量增加。
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公开(公告)号：KR101116029B1
公开(公告)日：2012-02-22
申请号：KR1020090085574
申请日：2009-09-10
Applicant: 국방과학연구소
Abstract: 본 발명은 원통형 시편의 내주면을 지지하며 내압의 증가에 의해 팽창되어 상기 원통형 시편에 원주 방향 하중을 가하는 팽창 튜브와, 상기 팽창 튜브의 내측 방향 팽창을 제한하도록 상기 팽창 튜브의 내주면을 지지하는 원환형 지지체와, 상기 팽창 튜브의 상하 방향 팽창을 제한하도록 상기 팽창 튜브의 상부 및 하부를 각각 지지하는 상부 및 하부 지지체를 포함하는 인장 시험 장치 및 이를 이용한 인장 시험 방법을 개시한다.
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Patent Agency Ranking
公开(公告)号：KR100947277B1
公开(公告)日：2010-03-11
申请号：KR1020080046299
申请日：2008-05-19
Applicant: 국방과학연구소
Abstract: 본 발명은 원통 형태로 형성된 시편의 축 방향을 따르는 압축 하중을 지지하며 상기 압축 하중에 의해 압축 방향으로 이동되는 지지부와, 상기 시편의 내주면에 지지되며 상기 지지부의 이동에 따라 상기 시편의 반경 방향으로 이동하여 상기 시편의 원주 방향으로 인장 변형을 가하는 이동부를 포함하는 인장 시험 장치에 관한 것으로서, 간단한 구조를 통하여 원통형 시편에 대해 원주 방향의 균일한 하중을 인가할 수 있는 인장 시험 장치를 제공함으로써, 원통형 시편의 원주 방향 인장을 정확하고 효율적으로 측정하기 위한 것이다.
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公开(公告)号：KR101375859B1
公开(公告)日：2014-03-17
申请号：KR1020130162917
申请日：2013-12-24
Applicant: 국방과학연구소
Abstract: A rear igniter mount provided by the present invention comprises supporting units, which have a ring shape to wrap around at least part of the rear igniter; an inner mount, which at least partly protrudes from the supporting units and is attached to the front of a nozzle neck of a rocket propulsion unit so that the rear igniter is fixed to the nozzle neck; and an outer mount, which has a ring shape corresponding to the inner mount with at least part of the outer mount so that the outer mount can be coupled to the inner mount and which adheres to the rear of the nozzle neck so that the inner mount is fixed to the nozzle neck, being attached to the front of the nozzle neck. The inner mount comprises a part, which is locked with the front of the nozzle neck; and a curve-shaped notch, which is destroyed between the supporting units of the rear igniter by the pressure generated from the ignition of the rear igniter. The inner mount is made of thermoplastic resin so that the notch is uniformly destroyed within a preset pressure range.
Abstract translation: 本发明提供的后点火装置包括支撑单元，其具有围绕后点火器的至少一部分的环形形状; 内部安装件，其至少部分地从支撑单元突出并附接到火箭推进单元的喷嘴颈部的前部，使得后部点火器固定到喷嘴颈部; 以及外部安装件，其具有与具有至少一部分外部安装件的内部安装件相对应的环形形状，使得外部安装件可联接到内部安装件并且附着到喷嘴颈部的后部，使得内部安装 被固定到喷嘴颈部，附接到喷嘴颈部的前部。 内部安装件包括与喷嘴颈部的前部锁定的部件; 以及由后点火器的点火产生的压力在后点火器的支撑单元之间被破坏的曲线形槽口。 内部支架由热塑性树脂制成，使得切口在预设的压力范围内均匀地被破坏。
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公开(公告)号：KR101875733B1
公开(公告)日：2018-07-09
申请号：KR1020170021846
申请日：2017-02-17
Applicant: 국방과학연구소
Abstract: 본발명은추진기관점화후 점화기가노즐목을빠져나가상기추진기관으로부터이탈하는후방점화용노즐기밀시스템에관한것으로서, 로켓추진기관의후방점화용노즐기밀시스템에있어서, 노즐목을포함하는노즐, 상기노즐목에배치되는후방점화기, 상기후방점화기를상기노즐목에고정시키도록적어도일부가상기노즐목에밀착되는후방점화기마운트, 점화신호를인가하도록상기후방점화기일단과연결되는점화케이블및 상기점화케이블의적어도일부가관통되는가시창을포함하고, 상기노즐의기밀을유지하도록상기노즐의일 측에결합되는노즐마개를포함하는것을특징으로하는후방점화용노즐기밀시스템을제공할수 있다.
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公开(公告)号：KR101097181B1
公开(公告)日：2011-12-21
申请号：KR1020110107702
申请日：2011-10-20
Applicant: 국방과학연구소
Abstract: PURPOSE: A variable rapid pressure rising rate simulator for a nozzle is provided to accurately simulate the inside of the combustion chamber of a nozzle since only high-pressure air with a flow rate controlled by a flow-rate control unit flows into a simulating unit. CONSTITUTION: A variable rapid pressure rising rate simulator for a nozzle comprises a flow-rate control unit(30), an opening unit(20), and a high-pressure gas generating unit(10). A nozzle(40) with a cap(45) is coupled to one side of the flow-rate control unit. The flow-rate control unit controls the amount of air and senses the change in pressure of a simulating unit(35) corresponding to the inside of the combustion pipe of a real nozzle. The opening unit is coupled to the other side of the flow-rate control unit and instantaneously discharges inner high-pressure air to the flow-rate control unit, if inner pressure rises to over a given value.
Abstract translation: 目的：提供一种用于喷嘴的可变快速升压速率模拟器，以精确地模拟喷嘴的燃烧室的内部，因为只有具有由流量控制单元控制的流量的高压空气流入模拟单元。 构成：用于喷嘴的可变快速升压速率模拟器包括流量控制单元（30），打开单元（20）和高压气体发生单元（10）。 具有盖（45）的喷嘴（40）联接到流量控制单元的一侧。 流量控制单元控制空气量并感测与实际喷嘴的燃烧管内部对应的模拟单元（35）的压力变化。 如果内压上升到超过给定值，则打开单元联接到流量控制单元的另一侧并且瞬时将内部高压空气排放到流量控制单元。
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公开(公告)号：KR1020090120326A
公开(公告)日：2009-11-24
申请号：KR1020080046299
申请日：2008-05-19
Applicant: 국방과학연구소
CPC classification number: G01N3/08 , G01N3/02 , G01N2203/0017 , G01N2203/0019 , G01N2203/0266
Abstract: PURPOSE: A tension test device and a manufacturing method thereof are provided to apply pure circumferential tensile strain to a cylindrical specimen by changing the axial compressive load of a cylindrical sample to the radial direction of a sample. CONSTITUTION: A tension test device is composed of a supporting unit(110) and a moving unit(120a). The supporting unit supports the axial compression load of a cylindrical sample. The supporting unit is moved to the compressed direction by the compression load. The moving unit is supported to the inner circumference of the sample. The moving unit is moved according to moving of the supporting unit. The moving unit circumferentially applies tensile strain to the sample.
Abstract translation: 目的：提供张力测试装置及其制造方法，通过将圆柱形样品的轴向压缩载荷改变到样品的径向方向，向圆柱形样品施加纯的周向拉伸应变。 构成：张力测试装置由支撑单元（110）和移动单元（120a）组成。 支撑单元支撑圆柱形样品的轴向压缩载荷。 支撑单元通过压缩载荷被移动到压缩方向。 移动单元被支撑在样品的内周。 移动单元根据支撑单元的移动而移动。 移动单元周向地对样品施加拉伸应变。
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