-
公开(公告)号：WO2012020960A2
公开(公告)日：2012-02-16
申请号：PCT/KR2011/005780
申请日：2011-08-09
CPC classification number: B64G1/10 , B64G1/428 , B64G1/50 , B64G1/546 , B64G2001/1092
Abstract: 본 발명은 격자 강화 복합재 구조를 이용한 우주용 다기능 구조체에 관한 것으로, 더욱 상세히는 첨단 우주용 구조체 기술로서, 기존의 위성 구조체가 하중지지 및 내부장비 보호에 국한된 기능만을 지닌데 비해, 구조기능, 전자기능, 열전달기능, 방사차폐, 전자기간섭차폐 기능을 갖추어 다양한 기능을 제공할 뿐만 아니라 무게절감과 공간활용도를 크게 향상한 격자 강화 복합재 다기능 구조체에 관한 것으로, 복수의 격자가 결합되어 형성된 격자 프레임과, 상기 격자 프레임의 일면에 접합되는 면재와, 상기 격자 프레임과 상기 면재에 의해 형성된 격자공간에 구비되어 전자기능을 수행하는 하나 이상의 전자 PCB와, 상기 전자 PCB에 구비되어 외부와의 전력분배 및 데이터전달을 위한 커넥터 및 상기 전자 PCB 간의 전기적 데이터 전달 및 전력분배를 위한 전기배선을 포함하여 구성되는 다기능 구조체를 제공한다.
Abstract translation: 这
本发明涉及到与电网的空间的多功能结构增强复合结构，更具体的结构技术的高空间，只有一个函数，特定于承重和内部设备保护的现有的卫星结构 相比于具有结构特征，电子功能，热功能，辐射屏蔽，它涉及电磁干扰，轻量化，以及提供一种屏蔽和配备特征和空间利用功能丰富的，较大的格栅增强改进的复合多功能结构体中，多个网格的 一个或多个电子PCB，设置在由格子框架和面材形成的格子空间中以执行电子功能; 用于与外部进行配电和数据传输的连接器，以及电子PCB和I / O之间的电气数据传输。 提供被配置为包括用于配电的电气布线的多官能团结构。
-
公开(公告)号：KR1020130033136A
公开(公告)日：2013-04-03
申请号：KR1020110097024
申请日：2011-09-26
CPC classification number: B64G1/443 , B64G1/222 , B64G2001/224 , H02S40/00
Abstract: PURPOSE: A hinge device for a satellite using a shape memory alloy and a satellite with the same are provided to minimize the deployed impact of the hinge device by removing the tradeoff between a deployment impact and rigidity after deployment. CONSTITUTION: A hinge device(30) for a satellite using a shape memory alloy comprises a first bracket(310), a second bracket(320), a tape spring hinge part(330), and a shape memory alloy cylinder fixing device(340). The first bracket is attached to one end of a satellite body by a coupling member or is attached to one end of panels if a solar cell panel is made of the multiple panels. The second bracket is attached to one end of the solar cell panel by a coupling member or is attached to one end of a panel adjacent to one end of a panel where the first bracket is attached if the solar cell panel is made of the multiple panels. The tape spring hinge part is arranged between the first and second brackets to deploy the second bracket against the first bracket. The tape spring hinge part elastically connects the first and second brackets and primarily fixes the first and second brackets after the deployment. After a shape memory alloy cylinder is deployed between the first and second brackets, the shape memory alloy cylinder fixing device secondarily fixes the first and second brackets.
Abstract translation: 目的：提供一种用于使用形状记忆合金的卫星和具有该形状记忆合金的卫星的铰链装置，以通过消除部署冲击和部署后的刚性之间的权衡来最小化铰接装置所部署的冲击。 构造：用于使用形状记忆合金的卫星的铰链装置（30）包括第一支架（310），第二支架（320），带弹簧铰链部分（330）和形状记忆合金圆筒固定装置（340） ）。 如果太阳能电池板由多个面板制成，则第一支架通过联接构件附接到卫星主体的一端或附接到面板的一端。 第二支架通过联接构件附接到太阳能电池板的一端，或者如果太阳能电池板由多个面板制成，则附接到邻近面板的一个端部的面板的一端附近的第一支架 。 带弹簧铰链部分布置在第一和第二支架之间，以将第二支架部署在第一支架上。 带弹簧铰链部分弹性地连接第一和第二支架，并且在部署之后主要固定第一和第二支架。 在形状记忆合金圆柱体部署在第一和第二托架之间之后，形状记忆合金圆筒固定装置二次固定第一和第二托架。
-
公开(公告)号：KR1020110076159A
公开(公告)日：2011-07-06
申请号：KR1020090132791
申请日：2009-12-29
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A mechanical ground support device is provided to transport, rotate and move an artificial satellite, to offer convenience and efficiency by performing various works using one structure, and to be structurally stable and simple against the load conditions added differently to an artificial satellite. CONSTITUTION: A mechanical ground support device comprises a movement support unit(110) attached to one side of an artificial satellite(10) and supporting the artificial satellite when moving the artificial satellite using a rope, a transportation support unit(120) supporting the movement support unit and functioning as a base when transporting the artificial satellite fixed to the movement support unit, and a rotation support unit(130) supported to the transportation support unit and attached to the other side of the artificial satellite to rotate the artificial satellite.
Abstract translation: 目的：提供一种用于运输，旋转和移动人造卫星的机械地面支撑装置，通过使用一种结构执行各种作品提供便利和效率，并且在结构上稳定和简单地抵抗与人造卫星不同的加载条件。 构成：机械地面支撑装置包括：移动支撑单元（110），其附接到人造卫星（10）的一侧并且在使用绳索移动人造卫星时支撑人造卫星;支撑运动的运输支撑单元（120） 支撑单元，并且当将固定在移动支撑单元上的人造卫星运送时作为基座起作用;以及旋转支撑单元，支撑在运输支撑单元上并附接到人造卫星的另一侧以旋转人造卫星。
-
公开(公告)号：KR101037346B1
公开(公告)日：2011-05-26
申请号：KR1020100076779
申请日：2010-08-10
Applicant: 한국항공우주연구원
CPC classification number: B64G1/10 , B64G1/428 , B64G1/50 , B64G1/546 , B64G2001/1092
Abstract: PURPOSE: A multi-functional structure for space using a lattice strengthened composite structure is provided to achieve weight reduction effect by removing the need of a separate housing for mounting an electronic PCB. CONSTITUTION: A multi-functional structure for space using a lattice strengthened composite structure comprises a lattice frame(10), a surface material(20), an electronic PCB(30), a connector(40), and electric wiring(50). The lattice frame is formed of a plurality of lattices(11). The surface material is attached to a side of the lattice frame. The electronic PCB is installed in a lattice space(21) formed by the lattice frame and the surface material and implements electronic functions. The connector is installed in the electronic PCB for power distribution and data communication with outside. The electric wiring is provided for electric data communication and power distribution in the electronic PCB.
Abstract translation: 目的：提供使用格子强化复合结构的空间多功能结构，以通过消除用于安装电子PCB的单独外壳的需要来实现减重效果。 构成：使用晶格加强复合结构的空间多功能结构包括格子框架（10），表面材料（20），电子PCB（30），连接器（40）和电线（50）。 网格框架由多个格子（11）形成。 表面材料附着在格子框架的一侧。 电子PCB安装在由格子框架和表面材料形成的格子空间（21）中，并实现电子功能。 连接器安装在电子PCB中，用于与外部配电和数据通信。 电气布线用于电子PCB中的电子数据通信和配电。
-
公开(公告)号：KR1020100037333A
公开(公告)日：2010-04-09
申请号：KR1020080096602
申请日：2008-10-01
Applicant: 한국항공우주연구원
IPC: B64C1/12
Abstract: PURPOSE: A bushing and a bushing assembly including the same are provided to improve the adhesion of the bushing to a structure by a knurled exterior surface of the bushing. CONSTITUTION: A bushing(30) guiding the assembly and mount of different structures comprises a bushing body(31) with a coupling hole(32), and a knurled part(34) formed on in the exterior surface to guide uniform spread of an adhesive for attachment of the bushing to the structures. The pitch interval of the knurled part is 1.0 to 1.4mm.
Abstract translation: 目的：提供一种套管和包括该衬套的衬套组件，以通过衬套的滚花外表面改善衬套与结构的粘合力。 构成：引导不同结构的组件和安装件的衬套（30）包括具有联接孔（32）的衬套主体（31）和形成在外表面上的滚花部分（34），以引导粘合剂的均匀铺展 用于将衬套附接到结构。 滚花部分的间距为1.0〜1.4mm。
-
Patent Agency Ranking
公开(公告)号：KR1020100020228A
公开(公告)日：2010-02-22
申请号：KR1020080078921
申请日：2008-08-12
Applicant: 한국항공우주연구원
IPC: B64G1/10
CPC classification number: B64G1/222 , B64G1/10 , B64G1/443 , B64G2001/224 , B64G2700/00
Abstract: PURPOSE: A hinge apparatus and a satellite having the same are provided to ensure development reliability in a simple structure wherein hinge brackets supporting the satellite body and a solar panel are connected with elastic members. CONSTITUTION: A first hinge bracket(40) is installed in a first unit. A second hinge bracket(50) is installed in a second unit. A connector(60) interlinks the first and second hinge brackets. The connector creates a restoring force in a folded state where the first and second units are faced each other. A coil spring is provided in the connector to gradually reduce the restoring force in the same direction as the second unit is opened with respect to the first unit.
Abstract translation: 目的：提供铰链装置和具有该铰链装置和卫星的卫星，以确保在简单结构中的开发可靠性，其中支撑卫星体和太阳能电池板的铰链支架与弹性构件连接。 构成：第一个铰链支架（40）安装在第一个单元中。 第二铰链支架（50）安装在第二单元中。 连接器（60）将第一和第二铰链支架相互连接。 连接器在第一和第二单元彼此面对的折叠状态下产生恢复力。 在连接器中设置有螺旋弹簧，以沿与第二单元相对于第一单元打开相同的方向逐渐减小恢复力。
-
公开(公告)号：KR101437875B1
公开(公告)日：2014-09-04
申请号：KR1020130094507
申请日：2013-08-09
Applicant: 한국항공우주연구원
Abstract: The present invention comprises: a main frame (100); a movable body (200) which is installed on the main frame (100) in order to move vertically and horizontally; a first fixating body (300) which is combined with the movable body (200), and detachably fixates one end of a tape spring (10); a second fixating body (400) which is placed at a fixed interval from the first fixating body (300) in the horizontal direction, and detachably fixates the other end of the tape spring (10) to a facing surface facing the first fixating body (300); a rotary body (500) which is combined with the second fixating body (400); and a measuring unit (600) which measures a hinge moment generated from the tape spring (10) by connecting the rotary body (500) with the main frame (100) in order to rotate the rotary body (500) and the second fixating body (400) through interlocking.
Abstract translation: 本发明包括：主框架（100）; 可移动体（200），其安装在主框架（100）上以便垂直和水平移动; 第一固定体（300），其与所述可动体（200）组合，并且可拆卸地固定所述带状弹簧（10）的一端; 第二固定体（400），其在水平方向上与第一固定体（300）以固定间隔放置，并且将带状弹簧（10）的另一端可拆卸地固定在面向第一固定体的面对面上 300）; 与第二固定体（400）组合的旋转体（500）; 以及测量单元（600），其通过将旋转体（500）与主框架（100）连接来测量从带状弹簧（10）产生的铰链力矩，以使旋转体（500）和第二固定体 （400）通过互锁。
-
8.发明公开형상기억합금 실린더와 형상기억합금 와이어를 이용한 저충격 비폭발식 분리장치, 그 분리장치의 설치방법, 분리시스템, 준비방법, 분리방법 및 재조립방법 有权使用形状记忆钢材料分离器和线路的分离装置和系统，用于设置装置的方法，使用装置的分离方法和使用装置的重新组合方法
公开(公告)号：KR1020120072475A
公开(公告)日：2012-07-04
申请号：KR1020100134239
申请日：2010-12-24
Abstract: PURPOSE: A low-shock and non-explosive release device using a shape memory alloy cylinder and a shape memory alloy wire, an installation method, a release system, a preparation method, a release method, and a re-assembling method thereof are provided to prevent pollution by reducing shock using a non-explosive method. CONSTITUTION: A low-shock and non-explosive release device comprises a shape memory alloy cylinder and a shape memory alloy wire(520). The shape memory alloy cylinder is composed of a shape memory alloy extended in an axial direction. The shape memory alloy wire is installed on a wire guide, and the ends of the shape memory alloy wire are fixed to outer holes. When the shape memory alloy wire is contracted, the shape memory alloy wire moves a trigger block(400) upward, and a center bolt(600) is stretched.
Abstract translation: 目的：提供使用形状记忆合金圆筒和形状记忆合金线的低冲击和非爆炸性释放装置，安装方法，释放系统，制备方法，释放方法和重新组装方法 通过使用非爆炸性方法减少冲击来防止污染。 构成：低冲击和非爆炸性释放装置包括形状记忆合金圆筒和形状记忆合金丝（520）。 形状记忆合金圆筒由沿轴向延伸的形状记忆合金构成。 形状记忆合金丝安装在导丝器上，形状记忆合金线的端部固定在外孔上。 当形状记忆合金线收缩时，形状记忆合金线将触发块（400）向上移动，中心螺栓（600）被拉伸。
-
公开(公告)号：KR101008047B1
公开(公告)日：2011-01-13
申请号：KR1020080070614
申请日：2008-07-21
Applicant: 한국항공우주연구원
IPC: B64G1/44
Abstract: 높은 전개강성을 가지며 열적으로 우수한 태양전지판 전개장치 및 이를 포함하는 인공위성이 개시된다. 개시된 본 발명에 의한 인공위성은, 인공위성 본체, 인공위성 본체와 연결되어, 태양광을 받아 인공위성 본체의 전력을 발생시키는 태양전지판, 그리고, 태양전지판을 인공위성 본체에 대해 전개시키는 전개장치를 포함한다. 여기서, 전개장치는, 인공위성 본체와 태양전지판을 상호 연결시키는 힌지유닛, 상호 대응되는 형상의 제 1 및 제 2 힌지브라켓을 가지고 인공위성 본체와 연결되는 제 1 전개유닛, 상호 대응되는 형상의 제 3 및 제 4 힌지브라켓을 가지고 태양전지판에 연결되는 제 2 전개유닛, 그리고, 제 1 및 제 2 전개유닛을 상호 접힘/전개 가능하게 연결하는 연결유닛을 포함한다. 이러한 구성에 의하면, 태양전지판이 인공위성 본체로부터 전개될 때 고강성을 가짐으로써, 인공위성의 빠른 안정화를 도모할 수 있다.
인공위성, 태양전지, 전개, 접힘, 펼쳐짐, 강성.-
公开(公告)号：KR101005260B1
公开(公告)日：2011-01-04
申请号：KR1020080078921
申请日：2008-08-12
Applicant: 한국항공우주연구원
IPC: B64G1/10
Abstract: 간단한 구조로 전개 신뢰성을 확보할 수 있는 힌지장치 및 이를 포함하는 인공위성이 개시된다. 개시된 본 발명에 의한 인공위성은, 인공위성 본체, 인공위성 본체와 연결되어, 태양광을 받아 인공위성 본체의 전력을 발생시키는 태양전지판, 그리고, 인공위성 본체와 태양전지판을 연결하는 힌지장치를 포함하며, 힌지장치는, 인공위성 본체에 설치되는 제 1 힌지브라켓, 태양전지판에 설치되는 제 2 힌지브라켓, 그리고, 제 1 및 제 2 힌지브라켓을 연결시키며, 인공위성 본체와 태양전지판이 상호 마주하는 접힘상태에서 복원력을 발생시키는 연결수단을 포함한다. 이에 의하면, 간단한 구조로 안정적인 전개를 구현할 수 있게 된다.
인공위성, 전개, 힌지, 연결, 스프링, 강성, 토크, 복원력.
-
-
-
-
-
-
-
-
-
Search Results
28
records
(took 0.021 seconds)
