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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.-
Patent Agency Ranking
公开(公告)号：KR1020030025407A
公开(公告)日：2003-03-29
申请号：KR1020010058348
申请日：2001-09-20
Applicant: 한국항공우주연구원
IPC: G05D1/00
Abstract: PURPOSE: A method for estimating latitude and longitude of a satellite using a CES(Conical Earth Sensor) is provided to estimate the latitude and the longitude of the satellite necessary for operating the satellite by using geocentric information and satellite attitude information of inertia coordinates. CONSTITUTION: A CES is used as an attitude control sensor of a satellite. The CES is used for measuring a relative attitude of satellite to earth by sensing infrared rays of 15 micro meter spectrum band emitted from earth. The device uses a principle that a vector of a center of earth to the satellite on inertia coordinates is identical to a vector obtained by converting a vector of the satellite to the center of earth measured by the CES to the inertia coordinate. The latitude and the longitude of the satellite are estimated by using the above principal of identification.
Abstract translation: 目的：提供一种使用CES（锥形地球传感器）估计卫星纬度和经度的方法，以通过使用地心信息和惯性坐标的卫星姿态信息来估计卫星运行所需的纬度和经度。 构成：CES被用作卫星的姿态控制传感器。 CES用于通过感测从地球发射的15微米谱带的红外线来测量卫星对地球的相对姿态。 该装置使用的原理是，惯性坐标上的卫星中心的向量与通过将卫星的矢量转换为惯性坐标测量的卫星的中心的矢量相同。 卫星的纬度和经度是通过使用上述识别原理来估计的。
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公开(公告)号：KR1020100047530A
公开(公告)日：2010-05-10
申请号：KR1020080106468
申请日：2008-10-29
Applicant: 한국항공우주연구원
CPC classification number: B64G1/40 , B64G2001/1092
Abstract: PURPOSE: A supporting body for a propulsion module of a satellite is provided to maintain the rigidity against a vibration even if the number of propulsion struts decreses. CONSTITUTION: A supporting body for a propulsion module of a satellite comprises a flat panel-shaped propulsion platform(100), a strut structure(200) and an adapter(300). The strut structure comprises a plurality of propulsion struts. The strut structure is combined with the top of the propulsion platform. The strut structure supports the propulsion tank of the satellite. The adapter comprises an adapter fitting(330). The adapter fitting enhances vibration characteristic by reinforcing rigidity. The adapter fitting is combined with the lower part of the propulsion platform.
Abstract translation: 目的：提供用于卫星推进模块的支撑体，以便即使推进支柱的数量减少，也能够抵抗振动的刚度。 构成：用于卫星推进模块的支撑体包括平板状推进平台（100），支柱结构（200）和适配器（300）。 支柱结构包括多个推进支柱。 支柱结构与推进平台的顶部结合。 支柱结构支持卫星的推进坦克。 适配器包括适配器配件（330）。 适配器配件通过增强刚度增强振动特性。 适配器配件与推进平台的下部组合。
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公开(公告)号：KR1020100009812A
公开(公告)日：2010-01-29
申请号：KR1020080070614
申请日：2008-07-21
Applicant: 한국항공우주연구원
IPC: B64G1/44
CPC classification number: B64G1/443 , B64G1/10 , B64G2001/224 , B64G2700/00 , F16F15/04
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：KR1020020032845A
公开(公告)日：2002-05-04
申请号：KR1020000063551
申请日：2000-10-27
Applicant: 한국항공우주연구원
IPC: H04B7/155
CPC classification number: H04W24/06 , H04L43/0805 , H04W84/06
Abstract: PURPOSE: A method for testing the compatibility between a satellite and a control system is provided to confirm the compatibility using an STB by producing a satellite before the satellite is directly produced, by verifying whether a flight software mounted to the satellite is suitable, and by verifying whether the software mounted is properly operated. CONSTITUTION: A control system is combined with an STB(Software Test Bed). The compatibility between the control system and a satellite is executed. A conversion software matches the control system with the satellite's protocol. The conversion software converts a telecommand packet transmitted from the control system into a CTLU packet. In addition, the conversion software receives a telemetering frame from the STB and makes the telemetering frame in a necessary form after removing a sync and a tail part. After that, the conversion software transmits the telemetering frame to the control system.
Abstract translation: 目的：提供一种用于测试卫星与控制系统之间的兼容性的方法，通过在卫星直接产生之前通过产生卫星来确认STB的兼容性，通过验证安装在卫星上的飞行软件是否合适，以及通过 验证安装的软件是否正常运行。 规定：控制系统与STB（软件测试床）相结合。 执行控制系统和卫星之间的兼容性。 转换软件将控制系统与卫星协议相匹配。 转换软件将从控制系统发送的遥控数据包转换成CTLU数据包。 此外，转换软件从STB接收遥测帧，并且在去除同步和尾部之后使得遥测帧成为必要的形式。 之后，转换软件将遥测帧发送到控制系统。
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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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