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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。
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公开(公告)号：KR1020130062532A
公开(公告)日：2013-06-13
申请号：KR1020110128832
申请日：2011-12-05
Applicant: 한국항공대학교산학협력단 , 한국항공우주연구원
Abstract: PURPOSE: A shock absorber using a permanent magnet is provided to generate a damping force and repulsive power using the effects of eddy currents and a magnetic force. CONSTITUTION: A shock absorber(100) using a permanent magnet comprises a support unit(50) and an excitation unit(90). The support unit absorbs the impact energy when an external shock is generated in a cylindrical shape. The support unit includes a composite pipe(10), a fixing pipe(20), a shaft, and a support permanent magnet. The composite pipe includes a steel panel, a copper pipe, and a pipe band. The fixing pipe is positioned on both sides of the composite pipe and fixes the state of connecting the composite pipe. The shaft is inserted into the inside of the excitation unit. The support permanent magnet is formed in the inner wall of the composite pipe and generates repulsive power when inserting the excitation unit. The excitation unit is inserted inside of the support unit and is dragged inside the support unit.
Abstract translation: 目的：提供使用永磁体的减震器，以利用涡流和磁力的作用产生阻尼力和排斥力。 构成：使用永磁体的减震器（100）包括支撑单元（50）和激励单元（90）。 当产生外部冲击时，支撑单元吸收冲击能量。 支撑单元包括复合管（10），固定管（20），轴和支撑永磁体。 复合管包括钢板，铜管和管带。 固定管位于复合管的两侧，固定连接复合管的状态。 轴插入励磁单元的内部。 支撑永磁体形成在复合管的内壁中，并且在插入激励单元时产生排斥力。 激励单元插入支撑单元内部并被牵引到支撑单元的内部。
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公开(公告)号：KR1020130060855A
公开(公告)日：2013-06-10
申请号：KR1020110127134
申请日：2011-11-30
Applicant: 한국항공대학교산학협력단 , 한국항공우주연구원
CPC classification number: B64G1/62 , B64G2001/1071
Abstract: PURPOSE: A deployment device for landing a space exploring satellite is provided to improve utilization of an inner space of the space exploring satellite by reducing a space occupied inside the space exploring satellite through supplying hinge rotation structure. CONSTITUTION: A deployment device for landing a space exploring satellite comprises a first support rod(100), a second support rod(200), a hinge bracket(300), and an elasticity deployment unit(400). The second support rod is installed to be rotated by the structure of the space exploring satellite. The hinge bracket connects the first support rod and the second support rod and is equipped on the first support rod and the second support rod to be hinge-rotated. The elasticity deployment unit surrounds the first support rod and rotates the second support rod and the hinge bracket with respect to the first support rod by elastically pressurizing the hinge bracket when the restricting state of the second support rod is released.
Abstract translation: 目的：提供用于着陆探空卫星的部署装置，通过减少通过提供铰链旋转结构探索卫星的空间，从而提高对探空卫星空间的利用。 构成：用于着陆探空卫星的展开装置包括第一支撑杆（100），第二支撑杆（200），铰链支架（300）和弹性展开单元（400）。 第二支撑杆安装成由探空卫星的结构旋转。 铰链支架连接第一支撑杆和第二支撑杆，并且装配在第一支撑杆和第二支撑杆上以进行铰链旋转。 当释放第二支撑杆的限制状态时，弹性展开单元围绕第一支撑杆并相对于第一支撑杆旋转第二支撑杆和铰链支架，弹性地对铰链支架施加压力。
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公开(公告)号：KR101306823B1
公开(公告)日：2013-09-26
申请号：KR1020110128832
申请日：2011-12-05
Applicant: 한국항공대학교산학협력단 , 한국항공우주연구원
Abstract: 본 발명은 스프링, 오일, 가스, 오리피스의 사용 없이 금속관을 내부에 영구자석을 배치하여, 와전류 감쇠와 마찰 감쇠 효과를 동시에 발휘하여, 충격에너지를 흡수할 수 있는 충격흡수장치에 관한 것으로, 본 발명에 따른 영구자석을 이용한 충격흡수장치는 전체적인 원형 관 형태로 외부 충격 발생 시, 충격에너지를 흡수하는 지지부 및 일측이 상기 지지부 내부로 삽입 결합되어, 외부 충격 발생 시, 상기 지지부 내부로 밀려들어가는 관 형태의 가진부를 포함하며, 상기 지지부는 두 가지 이상의 금속 재질로 구성된 복합관 및 상기 복합관의 일측 내벽에 형성된 지지영구자석을 포함하는 것을 특징으로 한다.
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公开(公告)号：KR101266970B1
公开(公告)日：2013-05-30
申请号：KR1020110127135
申请日：2011-11-30
Applicant: 한국항공대학교산학협력단 , 한국항공우주연구원
CPC classification number: B64G1/62 , B64G2001/1071
Abstract: PURPOSE: A deployment apparatus for landing a space exploration satellite is provided to increase the internal space utilization of the space exploration satellite because the installed space of the deployment apparatus is reduced by applying a hinge rotation structure. CONSTITUTION: A deployment apparatus for landing space exploration satellite comprises a first support rod(100), a second support rod(200), and an elastic rotation unit. The second support rod is installed to restrict the rotation by a structure of the space exploration satellite. The elastic rotation unit connects the first and second support rods and rotates the second support rod against the first support rod when the restriction of the second support rod is released.
Abstract translation: 目的：提供用于着陆空间探测卫星的部署装置，以增加空间探测卫星的内部空间利用，因为通过施加铰链旋转结构来减少展开装置的安装空间。 构成：着陆空间探测卫星的展开装置包括第一支撑杆（100），第二支撑杆（200）和弹性旋转单元。 安装第二支撑杆以通过空间探测卫星的结构限制旋转。 当释放第二支撑杆的限制时，弹性旋转单元连接第一和第二支撑杆并使第二支撑杆旋转抵靠第一支撑杆。
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Patent Agency Ranking
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。
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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。
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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。
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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。
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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。
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