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1. 发明授权

KR101898641B1 인공위성 및 이의 제어 방법 有权
公开(公告)号：KR101898641B1
公开(公告)日：2018-10-31
申请号：KR1020170103725
申请日：2017-08-16
申请人： 한국항공우주연구원
发明人： 전문진 , 최석원 , 임성빈
IPC分类号： B64G1/10 , B64G1/44 , B64G1/66 , B64G1/24 , H04N5/369 , H01L31/042 , H02S20/30
CPC分类号： B64G1/105 , B64G1/242 , B64G1/443 , B64G1/66 , B64G2001/1064 , H01L31/042 , H02S20/30 , H04N5/3692 , Y02E10/50
摘要： 본발명의다양한실시예들에따른인공위성과이의제어방법이제공된다. 인공위성은행성의궤도를따라비행하는본체, 상기본체에배치되고상기행성의지표(地表)를촬영하는광학탑재체, 및상기본체의제1 방향양 측에회전가능하게배치되는한 쌍의태양전지판을포함한다. 상기본체가비행하는비행방향과상기제1 방향은서로예각을이룬다.

2. 发明公开

KR20120074763A Active center of gravity and moment of inertia control device for geostationary earth orbit satellite having single solar array configuration 无效
标题翻译：具有单个太阳能阵列配置的地球环境卫星的主动控制装置的主动中心
公开(公告)号：KR20120074763A
公开(公告)日：2012-07-06
申请号：KR20100136700
申请日：2010-12-28
申请人： KOREA AEROSPACE RES INST
发明人： PARK KEUN JOO
IPC分类号： B64G1/28 , B64G1/44
CPC分类号： B64G1/28 , B64G1/443
摘要： PURPOSE: An active control method of gravity center and inertia moment for a geostationary earth orbit satellite having a single solar array configuration is provided to control posture and inertia moment of a satellite without waste of fuel by installing a first gravity center moving unit and a second gravity center moving unit inside a satellite body. CONSTITUTION: An active control method of gravity center and inertia moment for a geostationary earth orbit satellite having a single solar array configuration comprises a first gravity center moving unit(100) and a second gravity center moving unit(200). The first gravity center moving unit is installed inside a satellite body and varies the gravity center of the satellite body by slindingly moving along an axis. The second gravity center moving unit is installed inside the satellite body and is located in a coaxial line with the first gravity center moving unit. The second gravity center varies the gravity center of the satellite body by slidingly moving along the coaxial line with the first gravity center moving unit.
摘要翻译：目的：提供一种具有单一太阳能阵列结构的对地静止轨道卫星的重心和惯性矩的主动控制方法，通过安装第一重心移动单元和第二重心移动单元来控制卫星的姿态和惯性矩而不浪费燃料卫星体内的重心移动单元。构成：具有单个太阳能阵列结构的对地静止轨道卫星的重心和惯性矩的主动控制方法包括第一重心移动单元（100）和第二重心移动单元（200）。第一重心移动单元安装在卫星体内，并通过沿轴线滑动改变卫星的重心。第二重心移动单元安装在卫星体内，并且与第一重心移动单元位于同轴线上。第二重心通过沿着与第一重心移动单元的同轴线滑动地移动卫星体的重心。

3. 发明公开

KR20120057105A Supporting device for coil spring of solar panel hinge used in satellite 有权
标题翻译：支持用于卫星使用的太阳能电池板螺旋线圈的装置
公开(公告)号：KR20120057105A
公开(公告)日：2012-06-05
申请号：KR20100118699
申请日：2010-11-26
申请人： KOREA AEROSPACE RES INST
发明人： KIM KYUNG WON , LIM JAE HYUK , KIM SUN WON , HWANG DO SOON
IPC分类号： B64G1/44 , F16C11/04
CPC分类号： B64G1/443 , B64G1/222 , B64G2001/224 , F16C11/04
摘要： PURPOSE: A supporting device for mounting hinges of a solar panel hinge for a satellite using a coil spring is provided to accurately maintain a rotary shaft between two hinges by holding an accurate position of hinge brackets. CONSTITUTION: A supporting device for mounting hinges of a solar panel hinge for a satellite using a coil spring comprises two first hinge brackets(30), two second hinge brackets(40), and two connection units(50). Each first hinge bracket comprises a first coupling part(31) which is fixed and coupled to be separated from a satellite body at a fixed distance and a first bent part(32) which is bent from the first coupling unit at a right angle. Each second hinge bracket comprises a second coupling part(41) and a second bent part which is bent from the second coupling part at a right angle. Both ends of the connection units are respectively fixed in the first and second bent parts to connect the first and second hinge brackets. In a folded state where the satellite body and a solar panel face each other, the connection units generate restoration force.
摘要翻译：目的：提供一种用于安装用于使用螺旋弹簧的卫星的太阳能面板铰链的铰链的支撑装置，以通过保持铰链支架的精确位置来精确地保持两个铰链之间的旋转轴。构成：用于使用螺旋弹簧安装用于卫星的太阳能电池板铰链的铰链的支撑装置包括两个第一铰链支架（30），两个第二铰链支架（40）和两个连接单元（50）。每个第一铰链支架包括固定并联接成固定距离的卫星主体的第一联接部分（31）和从第一联接单元以直角弯曲的第一弯曲部分（32）。每个第二铰链支架包括第二联接部分（41）和第二弯曲部分，其从第二联接部分以直角弯曲。连接单元的两端分别固定在第一和第二弯曲部分中，以连接第一和第二铰链支架。在卫星体和太阳能电池板彼此面对的折叠状态下，连接单元产生恢复力。

4. 发明公开

KR1020100020218A 비대칭 위성 장치, 비대칭 위성의 모멘텀 덤핑 방법 및 비대칭 위성의 모멘텀 덤핑을 위한 회전각 설정방법 有权
标题翻译：不对称卫星设备，不对称卫星的旋转方法和旋转角度设置方法
公开(公告)号：KR1020100020218A
公开(公告)日：2010-02-22
申请号：KR1020080078909
申请日：2008-08-12
申请人： 한국전자통신연구원
发明人： 정성균 , 이상욱 , 김재훈
IPC分类号： B64G1/10 , B64G1/66
CPC分类号： B64G1/283 , B64G1/10 , B64G1/443 , B64G2700/00
摘要： PURPOSE: An asymmetric satellite apparatus, a momentum dumping method for an asymmetric satellite, and a rotation angle setting method for the momentum dumping method are provided to reduce the fuel consumption for momentum dumping by preventing the momentum accumulation occurring in the asymmetric satellite. CONSTITUTION: A solar panel(220) is asymmetrically connected to a satellite body. A weight reduction unit(230) including a fuel tank is positioned on the opposite side to the solar panel with respect to the center of mass of the satellite body and reduces the weight by discharging fuel from the fuel tank according to lapse of time.
摘要翻译：目的：提供一种不对称卫星装置，用于不对称卫星的动量倾倒方法和用于动量倾倒方法的旋转角度设定方法，以通过防止不对称卫星中发生的动量积累来减少动量倾倒的燃料消耗。构成：太阳能电池板（220）不对称地连接到卫星体上。包括燃料箱的重量减轻单元（230）相对于卫星体的质心位于太阳能电池板的相对侧，并且通过根据时间流逝从燃料箱排出燃料来减轻重量。

5. 发明公开

KR1020100009812A 태양전지판 전개장치 및 이를 포함하는 인공위성 有权
标题翻译：太阳能电池板解决方案和具有相同功能的人造卫星
公开(公告)号：KR1020100009812A
公开(公告)日：2010-01-29
申请号：KR1020080070614
申请日：2008-07-21
申请人： 한국항공우주연구원
发明人： 김경원 , 김선원 , 임재혁 , 이주훈 , 황도순 , 송운형 , 최항석 , 김진희 , 진익민 , 김학정
IPC分类号： B64G1/44
CPC分类号： B64G1/443 , B64G1/10 , B64G2001/224 , B64G2700/00 , F16F15/04
摘要： PURPOSE: A solar cell panel unfolding device and an artificial satellite having the same are provided to improve the rigidity of the solar cell panel unfolding device by unfolding the solar panel in the artificial satellite main body. CONSTITUTION: A hinge unit connects the artificial satellite main body and a solar panel. A first unfolding unit(120) has two hinge brackets(121,124) which are mutually corresponded shape. The first unfolding unit is connected to the artificial satellite main body. A second unfolding unit(140) has third and fourth hinge brackets(141,144). The second unfolding unit is connected to the solar panel. A connecting unit(160) folds or unfolds the first and second unfolding units.
摘要翻译：目的：提供一种太阳能电池板展开装置和具有该太阳能电池板展开装置的人造卫星，以通过在人造卫星主体中展开太阳能电池板来提高太阳能电池板展开装置的刚度。构成：铰链单元连接人造卫星主体和太阳能电池板。第一展开单元（120）具有相互对应的形状的两个铰链支架（121,124）。第一展开单元连接到人造卫星主体。第二展开单元（140）具有第三和第四铰链支架（141,144）。第二展开单元连接到太阳能电池板。连接单元（160）折叠或展开第一和第二展开单元。

6. 发明授权

KR100835656B1 태양전지판의 전개 동작 모사장치 失效
标题翻译：太阳能阵列的部署测试装置
公开(公告)号：KR100835656B1
公开(公告)日：2008-06-05
申请号：KR1020070081332
申请日：2007-08-13
申请人： 한국항공우주연구원
发明人： 이동우 , 문상무 , 임종민 , 문남진 , 은희광
IPC分类号： B64G1/44
CPC分类号： B64G7/00 , B64G1/443
摘要： A deployment test apparatus of a solar array is provided to perform a deployment test of the solar array at low cost by moving a moving bar in a minimum friction resistance state to deploy the solar array in a gravity-free state similar to space. A deployment test apparatus(1) of a solar array(170) includes a driving unit(100), a moving bar(230), and a guide frame(220). The driving unit has a plurality of solar arrays, a connecting shaft, a driving shaft(140), a plurality of pulleys, a belt(130), and a motor(120). The solar arrays are deployed on a base frame(110) by floating on the air. The connecting shaft is rotatably coupled with connecting units of the adjacent solar arrays. The driving shaft is rotatably installed on the base frame and fixes one end of the one side solar array thereto. The pulleys are rotatably installed on the driving shaft and the connecting shaft respectively. Some pulleys installed on the connecting shaft are coupled with the solar array, and others are coupled with the connecting shaft. The belt connects the pulleys. The motor rotates the driving shaft to deploy the solar arrays. The moving bar is connected to some or all of the solar arrays by support cables(270) to support the solar arrays. Both ends of the moving bar are moved on the guide frame.
摘要翻译：提供一种太阳能电池阵列的部署测试装置，通过在最小的摩擦阻力状态下移动移动的杆来以低成本执行太阳能阵列的部署测试，以将太阳能阵列部署在类似于空间的无重力状态。太阳能阵列（170）的部署测试装置（1）包括驱动单元（100），移动杆（230）和引导框架（220）。驱动单元具有多个太阳能阵列，连接轴，驱动轴（140），多个滑轮，皮带（130）和马达（120）。太阳能电池阵列通过浮在空中而部署在基架（110）上。连接轴与相邻太阳能阵列的连接单元可旋转地连接。驱动轴可旋转地安装在基架上并将一侧太阳能电池阵列的一端固定在其上。滑轮分别可旋转地安装在驱动轴和连接轴上。安装在连接轴上的一些滑轮与太阳能阵列耦合，而其它滑轮与连接轴联接。皮带连接皮带轮。电机旋转驱动轴以部署太阳能电池阵列。移动杆通过支撑电缆（270）连接到一些或所有太阳能阵列以支撑太阳能阵列。移动杆的两端在引导框架上移动。

7. 发明公开

KR1020180052274A 우주 쓰레기 제거용 위성 有权
公开(公告)号：KR1020180052274A
公开(公告)日：2018-05-18
申请号：KR1020160149407
申请日：2016-11-10
申请人： 한국항공우주연구원
发明人： 최준민
IPC分类号： B64G1/66 , B64G1/52 , B64G1/40 , B64G1/24 , B64G1/10
CPC分类号： B64G1/24 , B64G1/10 , B64G1/222 , B64G1/242 , B64G1/44 , B64G1/443 , B64G1/56 , B64G1/641 , B64G1/66 , B64G2001/245 , G05D1/0883 , B64G1/40 , B64G1/52
摘要： 일실시예에따른우주쓰레기제거용위성은, 위성본체; 상기위성본체의외측면에접힘가능하고, 우주쓰레기를향하여배치되어상기우주쓰레기의이동속도를감소시키는방패부재; 및상기위성본체에대하여상기방패부재를지지하는지지부재;를포함하고, 상기방패부재는, 상기위성본체의일면에겹쳐지는중앙패널; 상기중앙패널의측면에연결되어, 방사상방향으로연장되는복수개의제1 패널; 및상기복수개의제1 패널사이에연결된복수개의제2 패널;을포함할수 있다.

8. 发明公开

KR1020170037551A 전개가능한 어셈블리 审中-实审
标题翻译：可展开组装
公开(公告)号：KR1020170037551A
公开(公告)日：2017-04-04
申请号：KR1020160122294
申请日：2016-09-23
申请人： 탈레스
发明人： 뒤까르네줄리앙 , 그라브줄리앙 , 뢰떼노예르사비에
IPC分类号： H02S20/30 , H02S30/00 , H01L31/05
CPC分类号： B64G1/222 , B64G1/10 , B64G1/44 , B64G1/443
摘要： 본발명은지지구조부 (25), 패널들 (21, 22) 의세트 (20) 로서, 패널들 (21, 22) 의각각은중간회전축을규정하는힌지에의해인접한패널에연결되며, 패널들 (21, 22) 이다른패널위에접혀져있는적재구성으로부터, 각각의중간회전축들에대한패널들 (21, 22) 의회전에의해, 패널들이실질적으로동일한평면에배열되는전개구성으로전환할수 있는전개구성으로전환할수 있는, 상기패널들의세트, 지지구조부 (25) 에대한패널들 (21, 22) 의세트 (20) 의메인회전축을규정하는관절디바이스 (26) 를포함하는전개가능한어셈블리 (30) 에관한것이다. 본발명에따르면, 패널들 (21, 22) 의세트 (20) 는적재구성으로부터전개구성으로전환하기위해패널들의세트가중간회전축들및 메인회전축에대해회전이동하고, 패널들 (21, 22) 의세트 (20) 는지지구조부 (25) 에대해패널들 (21, 22) 의세트 (20) 를배향하기위해전개구성에서메인회전축에대해단지회전이동가능하다.
摘要翻译：本发明，每个支撑结构25中，一组面板21的20和22，所述面板（21，22）连接到限定的中间旋转轴，所述面板（通过铰链相邻的面板 21，22）是从所述上面板的折叠的堆叠配置的不同，对于每个中间旋转轴（21，22）的面板开发出可通过国会配置之前切换到展开构型，所述面板被布置成基本上在同一个平面开关可以在可部署组件30包括限定所述面板（21，22）用于该组的组（20）的主旋转轴的铰接装置26，该面板的支承结构部分（25）会的。根据本发明，所述面板（21，22）组20是一组面板，切换到从neunjeok展开构重构动绕中间旋转轴和旋转的主轴线，并且面板21和22 组20仅能够以定向板（21，22），用于地球解调器25的置位（20）绕在展开构造中旋转的主轴的运动。

9. 发明授权

KR101474471B1 인공위성 모니터링 장치 有权
标题翻译：监测卫星的装置
公开(公告)号：KR101474471B1
公开(公告)日：2014-12-22
申请号：KR1020130075817
申请日：2013-06-28
申请人： 한국항공우주연구원
发明人： 원영진 , 박홍원 , 문홍열 , 우성현 , 김진희
IPC分类号： B64G1/44 , B64G1/66 , G01B7/30
CPC分类号： B64G3/00 , B64G1/443 , B64G1/66 , B64G2001/224 , B64G2700/66
摘要： 본 발명은 인공위성 모니터링 장치에 관한 것으로서, 이 장치는, 제1 및 제2 디스크, 입력 전압을 제공하는 전원부, 제1 디스크의 일면에 나란히 배치되며 일단이 입력 전압에 연결되는 복수의 저항, 저항 양단에 연결되어 있으며 상기 제1 디스크 바깥쪽으로 돌출되어 있는 복수의 볼 베어링, 제2 디스크의 일면에 나란히 배치되며 복수의 저항을 순차적으로 연결할 수 있도록 볼 베어링과 접촉하는 복수의 저항 모듈 접촉판을 포함한다.
摘要翻译：卫星监视装置技术领域本发明涉及卫星监视装置。该装置包括第一和第二盘，提供输入电压的电源部分; 多个电阻布置在第一盘的一个表面上并具有连接到输入电压的一端; 多个滚珠轴承，其连接到电阻的两端并突出到第一盘的外部; 以及多个电阻模块接触板，其布置在第二盘的一个表面上并且接触球轴承以连续地连接电阻。

10. 发明授权

KR101468997B1 테잎 스프링 힌지와 코일 스프링 힌지를 이용한 인공위성용 전개장치 有权
标题翻译：卫星使用弹簧弹簧铰链和线圈弹簧铰链部署装置
公开(公告)号：KR101468997B1
公开(公告)日：2014-12-04
申请号：KR1020130101603
申请日：2013-08-27
申请人： 한국항공우주연구원
发明人： 김경원 , 임재혁 , 김선원 , 김창호 , 김성훈
IPC分类号： B64G1/44 , F16C11/00
CPC分类号： B64G1/443 , B64G2001/224 , H02S30/20
摘要： 본 발명은 태양 전지판 사이에 구비되며, 상기 태양 전지판 사이의 각도를
변화시켜 전개하는 인공위성용 전개장치에 있어서, 높이 방향으로 형성된 복수개의 테잎 스프링 힌지와 상기 테잎 스프링 힌지 사이에 개재되어 배치되는 코일 스프링 힌지과 상기 테잎 스프링 힌지 및 상기 코일 스프링 힌지의 양단에 각각 구비되어 태양 전지판과 연결하는 연결부재를 포함하여 이루어지는 테잎 스프링 힌지와 코일 스프링 힌지를 이용한 인공위성용 전개장치에 관한 것이다.
摘要翻译：本发明涉及一种安装在太阳能电池板之间并通过改变太阳能电池板之间的角度部署的卫星的展开装置，涉及一种使用带弹簧铰链和螺旋弹簧铰链的卫星展开装置，包括：在高度方向上形成的多个带状弹簧铰链; 螺旋弹簧铰链，布置成插入在带弹簧铰链之间; 以及分别安装在带弹簧铰链和螺旋弹簧铰链的两端并连接太阳能电池板的连接构件。

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