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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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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：KR101495246B1
公开(公告)日：2015-02-25
申请号：KR1020140032589
申请日：2014-03-20
CPC classification number: B64G1/222 , B64G1/10 , B64G1/64 , B64G2001/224
Abstract: 전개장치의 일 실시예는, 하나는 인공위성에 연결되고 다른 하나는 전개형 구조물에 연결되는 한 쌍의 브라켓과, 상기 한 쌍의 브라켓 사이를 연결하고 상기 전개형 구조물을 전개하도록 벤딩된 상태에서 전개되는 탄성체를 포함하는 힌지부; 일측이 상기 한 쌍의 브라켓 중 어느 하나에 결합하고, 상기 힌지부의 탄성체가 벤딩상태에서 전개되는 경우 소성변형하면서 상기 힌지부의 전개속도를 줄이는 감쇠부를 포함할 수 있다.
Abstract translation: 展开装置的实施例可以包括：铰链单元，其包括一对托架，其中一个托架连接到人造卫星，另一个连接到展开型结构，弹性体连接该对托架并展开在 弯曲以展开展开型结构; 以及减少单元，其一侧要组合在一对托架中的任一个中，并且如果铰链单元的弹性体弯曲地展开，则可塑性变换期间降低铰链单元的展开速度。
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公开(公告)号：KR1020140052347A
公开(公告)日：2014-05-07
申请号：KR1020120118365
申请日：2012-10-24
Applicant: 한국항공우주연구원
CPC classification number: Y02A40/252 , Y02A40/266 , Y02A40/268 , Y02E10/46 , Y02P60/124 , A01G9/24 , A01G9/14 , A01G9/1438 , A01G9/241 , F03G6/00 , F24S50/20 , Y02E10/52
Abstract: Disclosed are a ventilation window and a photovoltaic greenhouse having the same. According to an embodiment of the present invention, multiple ventilation holes though which internal air and external air pass are formed on the ventilation window, to enable easy ventilation. In addition, the multiple ventilation holes can have a downward slope in the direction of the outside. According to an embodiment of the present invention, the photovoltaic greenhouse can include the described ventilation window and a solar cell module which converts sunlight to electric power. Multiple cylinders are provided with piston rods which are joined to each corner of a back side of the solar cell module to be able to rotate in any direction. The solar cell module is able to trace the sun by the rotations of the multiple cylinders in any direction (upward, downward, left and right).
Abstract translation: 公开了一种通风窗和具有该通风窗的光伏温室。 根据本发明的一个实施例，通风窗上形成有内部空气和外部空气通过的多个通风孔，以便于通风。 此外，多个通风孔可以在外部的方向上具有向下的倾斜。 根据本发明的实施例，光伏温室可以包括所描述的通风窗和将太阳光转换为电力的太阳能电池模块。 多个气缸设置有活塞杆，活塞杆连接到太阳能电池模块的后侧的每个角以能够在任何方向上旋转。 太阳能电池模块能够通过多个气缸在任何方向（向上，向下，向左和向右）的转动来追踪太阳。
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5.发明授权인공위성 구조체의 본체 및 추진 모듈 조립용 치공구,탑재 모듈 조립용 치공구, 및 인공위성 구조체 조립용치공구 失效用于组装设备模块和推进模块的夹具，以及航天器结构的有效载荷模块和用于组装航天器结构的夹具
公开(公告)号：KR100537562B1
公开(公告)日：2005-12-19
申请号：KR1020030094489
申请日：2003-12-22
Applicant: 한국항공우주연구원
IPC: B64F5/00
Abstract: 본 발명은 인공위성 구조체 부품을 도면 요구 조건에 정확히 일치하도록 위치시키며, 또한 각 구조 모듈별로 동시에 조립이 진행될 수 있도록 하는 인공위성 구조체 조립용 치공구에 관한 것이다.
본 발명의 인공위성 구조체 조립용 치공구는 본체 및 추진 모듈용 조립 치공구와 탑재 모듈 조립용 치공구로 나누어져 있다. 각 모듈 조립 치공구는 수평을 유지하기 위한 하부 구조물과, 구조 부품의 위치를 정확히 잡아주기 위한 조립 치공구와, 각 구조 부품간의 연결을 위한 구멍가용 치공구와의 결합 및 상단부의 이동용 구조 부품을 갖는 것을 특징으로 한다.
본 발명은 모듈별 조립 후에 총 조립을 수행하는 병렬적인 인공위성 구조체 조립을 가능하게 하여, 총 조립 시간을 단축하고 총 조립을 용이하게 한다.-
Patent Agency Ranking
公开(公告)号：KR100489740B1
公开(公告)日：2005-05-16
申请号：KR1020020071592
申请日：2002-11-18
Applicant: 한국항공우주연구원
IPC: B64G1/44
Abstract: 본 발명은 인공위성에 사용되는 태양전지판을 연결하고 발사시 태양전지판을 접힌 상태로 유지시킨 후 임무궤도에서 태양전지판을 캠 플레이트 전개방식으로 전개시키는 역할을 수행하는 캠 플레이트 구동 방식의 인공위성 태양전지판 전개 장치에 관한 것이다.
이러한 본 발명은 돌출된 플랜지부분에 외측으로 로울러(6)가 설치되고 안쪽으로 정지몸체(7)가 설치되며 반대쪽에 라체터(11)를 설치한 상측 브래킷(1)과,
상기 상측 브래킷(1)과 하측 브래킷(2)의 플랜지부분에서 회전 가능하게 연결하는 회전축(4)과,
상기 상측 브래킷(1)과 회전축(4)으로 연결되며 태양전지판에 고정되는 하측 브래킷(2)과,
상기 하측 브래킷(2)의 플랜지부 하측으로 토셔널 스프링(10)이 삽입되어 있어 회전동력을 제공하는 드라이빙 축(9)과,
상기 드라이빙 축(9)의 일측 선단에 연결되며 로울러(6)가 삽입되는 장공(3')을 갖는 캠 플레이트(3)로 구성됨을 특징으로 하는 것이다.-
公开(公告)号：KR100468311B1
公开(公告)日：2005-01-27
申请号：KR1020020071591
申请日：2002-11-18
Applicant: 한국항공우주연구원
IPC: G01N3/00
Abstract: PURPOSE: An apparatus for testing strength of a strain energy type hinge is provided to obtain a strength value of the strain energy type hinge by measuring a displacement of a strength beam in a data measurement system. CONSTITUTION: A hinge section(8) is connected to a panel(80) of a solar cell plate. The hinge section(8) is provided with a connection member(82), which is fixed to the panel(80) by means of a fixing pin(81). A hinge(83) is provided between connection members(82). A route hinge is provided between a satellite and the solar cell plate. A hinge fixing terminal is installed at one side of a surface plate. The hinge fixing terminal has a rigid block structure. A fixing bracket is fixedly coupled to the connection member(82) of the hinge(8).
Abstract translation: 目的：提供一种用于测试应变能型铰链的强度的设备，以通过测量数据测量系统中的强度束的位移来获得应变能类型铰链的强度值。 构成：铰链部分（8）连接到太阳能电池板的面板（80）。 铰链部分8设置有连接部件82，该连接部件82通过固定销81固定在面板80上。 铰链（83）设置在连接构件（82）之间。 在卫星和太阳能电池板之间提供路线铰链。 铰链固定端子安装在平台的一侧。 铰链固定端子具有刚性块结构。 固定支架固定地联接到铰链（8）的连接构件（82）。
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公开(公告)号：KR100400977B1
公开(公告)日：2003-10-10
申请号：KR1020000079452
申请日：2000-12-21
Applicant: 한국항공우주연구원
IPC: G01M99/00
Abstract: PURPOSE: An apparatus is provided to allow a user to observe, on the earth, the explosion of solar cell panel mounted to an artificial satellite, in the cosmos, through the apparatus with simplified structure and reduced cost, while improving reliability for test. CONSTITUTION: An apparatus comprises a solar cell panel(3); an explosion structure connected to the solar cell panel; a bungee cable arranged to a guide beam(12) for implementing gravity-free state on the earth, and which explodes the solar cell panel; an adiabatic box for providing a low temperature environment by supplying a low temperature nitrogen gas(20) through a nitrogen liquid tank(17), an evaporator(18) and a nitrogen gas supply pump(19); and a power controller(22) and a power supply(21) connected to a heater so as to operate an extra small friction bearing.
Abstract translation: 目的：提供一种装置，使得用户能够通过该设备在地球上观察安装在人造卫星上的太阳能电池板的爆炸，其结构简化且成本降低，同时提高了测试的可靠性。 构成：一种装置包括太阳能电池板（3）; 连接到太阳能电池板的爆炸结构; 布置在引导梁（12）上的用于在地球上实现无重力状态并且使太阳能电池板爆炸的蹦极电缆; （17），蒸发器（18）以及氮气供给泵（19）供给低温氮气（20）来提供低温环境的绝热箱。 以及连接到加热器的电源控制器（22）和电源（21），以便操作额外的小摩擦轴承。
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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。
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公开(公告)号：KR1020040043357A
公开(公告)日：2004-05-24
申请号：KR1020020071591
申请日：2002-11-18
Applicant: 한국항공우주연구원
IPC: G01N3/00
Abstract: PURPOSE: An apparatus for testing strength of a strain energy type hinge is provided to obtain a strength value of the strain energy type hinge by measuring a displacement of a strength beam in a data measurement system. CONSTITUTION: A hinge section(8) is connected to a panel(80) of a solar cell plate. The hinge section(8) is provided with a connection member(82), which is fixed to the panel(80) by means of a fixing pin(81). A hinge(83) is provided between connection members(82). A route hinge is provided between a satellite and the solar cell plate. A hinge fixing terminal is installed at one side of a surface plate. The hinge fixing terminal has a rigid block structure. A fixing bracket is fixedly coupled to the connection member(82) of the hinge(8).
Abstract translation: 目的：提供一种用于测试应变能类型铰链的强度的装置，以通过测量数据测量系统中强度梁的位移来获得应变能型铰链的强度值。 构成：铰链部分（8）连接到太阳能电池板的面板（80）。 铰链部分（8）设置有通过固定销（81）固定到面板（80）的连接构件（82）。 铰链（83）设置在连接构件（82）之间。 在卫星和太阳能电池板之间提供路线铰链。 铰链固定端子安装在表面板的一侧。 铰链固定端子具有刚性块结构。 固定支架固定地联接到铰链（8）的连接构件（82）上。
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