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公开(公告)号：KR1020030094457A
公开(公告)日：2003-12-12
申请号：KR1020020031312
申请日：2002-06-04
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A solar cell plate unfolding test apparatus for low temperature condition verification is provided to be capable of easily and smoothly unfolding a solar cell plate without friction according to the unfolded angle and direction of the solar cell plate. CONSTITUTION: A solar cell plate unfolding test apparatus for low temperature condition verification is provided with a fixing part(5), a pillar(34) protruded from the center portion of the fixing part, a solar cell plate fixing part(3) connected with the pillar for fixing a solar cell plate(4), a joint shaft(20) protruded from the upper portion of the solar cell plate fixing part, and a controlling part(2) located at the upper portion of the joint shaft and connected with a bearing housing through a bearing(24). The solar cell plate unfolding test apparatus further includes an Al profile portion(10) connected with the bearing housing, an LM shaft(11) installed at the lower portion of the Al profile portion, and solar cell unfolding part(1) for moving itself according to the unfolded angle of the solar cell plate.
Abstract translation: 目的：提供一种用于低温条件验证的太阳能电池板展开试验装置，其能够根据太阳能电池板的展开角度和方向，容易且平滑地展开太阳能电池板而不产生摩擦。 构成：用于低温条件验证的太阳能电池板展开试验装置设置有固定部分（5），从固定部分的中心部分突出的支柱（34），太阳能电池板固定部分（3），与太阳能电池板固定部分 用于固定太阳能电池板（4）的支柱，从太阳能电池板固定部分的上部突出的关节轴（20）和位于关节轴的上部的控制部分（2） 通过轴承（24）的轴承壳体。 太阳能电池板展开试验装置还包括与轴承壳体连接的Al型材部分（10），安装在铝型材部分的下部的LM轴（11）和用于移动自身的太阳能电池展开部分（1） 根据太阳能电池板的展开角度。
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公开(公告)号：KR1020120057162A
公开(公告)日：2012-06-05
申请号：KR1020100118783
申请日：2010-11-26
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A device for measuring a center of gravity and a moment of inertia and a method for measuring the center of gravity and the moment of inertia using the same are provided to reduce manufacturing costs and to simplifying a structure by measuring a center of gravity and a moment of inertia with one device without moving or installing a measurement object. CONSTITUTION: A device for measuring a center of gravity and a moment of inertia comprises a measuring table(110), a first shaft(120), a second shaft(140), a pivot(150), a bearing(160), a force sensor(170), a fixing unit(180), and a driving unit(190). The measuring table supports measurement objects. The pivot supports the second shaft to be pivotable so that the first and second shafts are inclined by an offset of a center of gravity of the measurement objects. The bearing is installed in the outer circumference of the first shaft so that the first shaft is relatively rotated and supports a moment generated caused by the first and second shafts being inclined. The force sensor supports the bottom surface of the bearing and measures a reaction force with respect to the bearing generated caused by the first and second shafts being inclined. The driving unit generates torsion in a torsion bar by rotating the first shaft when the second shaft is fixed.
Abstract translation: 目的：提供一种用于测量重心和惯性矩的装置以及用于测量重心的方法和使用其的惯性力矩以降低制造成本并通过测量重心来简化结构， 没有移动或安装测量对象的一个设备的惯性矩。 结构：用于测量重心和惯性矩的装置包括测量台（110），第一轴（120），第二轴（140），枢轴（150），轴承（160），轴承 力传感器（170），固定单元（180）和驱动单元（190）。 测量表支持测量对象。 枢轴支撑第二轴可枢转，使得第一和第二轴由测量对象的重心的偏移倾斜。 所述轴承安装在所述第一轴的外周中，使得所述第一轴相对旋转并且支撑由所述第一和第二轴产生的力矩倾斜。 力传感器支撑轴承的底表面并且测量相对于由第一和第二轴倾斜产生的轴承的反作用力。 驱动单元通过在第二轴固定时旋转第一轴而在扭杆中产生扭转。
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13.发明授权
公开(公告)号：KR101134111B1
公开(公告)日：2012-04-09
申请号：KR1020090119521
申请日：2009-12-04
Applicant: 한국항공우주연구원
Abstract: 본 발명은 분사구 하단면에 측면으로 연장되는 연장부를 갖는 추력기 노즐의 분사구에 설치되는 것으로서, 원형체로 형성되어 상기 연장부의 후방면과 맞닿도록 설치되되, 중앙에 통공이 형성되는 브라켓과, 상기 브라켓에 설치되어 브라켓과 추력기 노즐을 고정하는 고정수단과, 상기 브라켓의 통공에 끼워져 회전가능하게 설치되되, 일측이 브라켓의 외측으로 돌출되는 노즐핀과, 육면체로 형성되어 상부면이 상기 브라켓의 외측으로 돌출된 노즐핀의 일측과 결합되되, 측면 중 어느 한 면과 그에 인접한 다른 한 면의 외측에 미러가 형성되는 미러고정체를 포함하는 것을 특징으로 한다.
본 발명에 의하면, 미러가 설치되는 미러고정체를 육면체로 형성하고 회전 가능하도록 설치하여 데오드라이트의 측정각도 한계로 인해 기존 방법으로는 측정이 불가능한 방향의 노즐을 본 발명을 이용해 측정할 수 있으며, 공간적인 제약을 최소화함으로써 최소한의 공간만으로도 추력기 노즐의 정확한 3차원 좌표를 측정할 수 있는 효과가 있다.
추력기 노즐, 얼라인먼트, 미러, 데오드라이트-
14.发明公开
公开(公告)号：KR1020110062712A
公开(公告)日：2011-06-10
申请号：KR1020090119521
申请日：2009-12-04
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A mirror fixing device for measuring alignment of thruster is provided to measure the coordinate of a thruster nozzle by making a mirror fixing device in rotary cube. CONSTITUTION: A mirror fixing device for measuring alignment of thruster comprises a bracket(200), a fixing member(300), a nozzle pin(400), and a mirror fixture(500). The bracket is formed in circular body and installed to meet the rear side of an extension part. A through hole is formed on the center of the bracket. The fixing device is installed in the bracket to fix the bracket and thruster nozzle. The nozzle pin is inserted in the through hole of bracket and pivotally establishes. One side of the nozzle pin is projected to the outside of bracket. The mirror fixture is formed in cube and is combined with one side of the nozzle pin. The mirror fixture has a mirror.
Abstract translation: 目的：提供一种用于测量推进器对准的镜面固定装置，通过将反光镜固定装置制成旋转立方体来测量推进器喷嘴的坐标。 构成：用于测量推进器对准的镜面固定装置包括支架（200），固定构件（300），喷嘴销（400）和反射镜固定件（500）。 支架形成为圆形体，并安装成与延伸部分的后侧相接。 在支架的中心形成通孔。 固定装置安装在支架上以固定支架和推进器喷嘴。 喷嘴销插入托架的通孔中并枢转。 喷嘴销的一侧突出到支架的外侧。 镜子夹具形成立方体，并与喷嘴销的一侧相结合。 镜子夹具有一个镜子。
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公开(公告)号：KR100835656B1
公开(公告)日：2008-06-05
申请号：KR1020070081332
申请日：2007-08-13
Applicant: 한국항공우주연구원
IPC: B64G1/44
Abstract: 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.
Abstract translation: 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。
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Patent Agency Ranking
公开(公告)号：KR1020060075115A
公开(公告)日：2006-07-04
申请号：KR1020040113678
申请日：2004-12-28
Applicant: 한국항공우주연구원
IPC: G10K11/16
CPC classification number: G10K11/175 , G10K2210/12 , G10K2210/3032
Abstract: 본 발명은 잔향실 내의 소리신호 중에 저주파 소리신호의 위상을 반전시켜 고주파 소리신호를 유지시키고 저주파 소리신호만을 상쇄시킬 수 있는 흡음 장치를 제공하는 것으로, 잔향실 내의 소리신호를 입력받아 아날로그 전기신호를 출력하는 마이크로폰; 마이크로폰으로부터 출력되는 아날로그 전기신호를 디지털 신호로 변환시키고 변환한 디지털 신호를 위상 천이시킨 후 위상 천이된 디지털 신호 중에 일정 주파수대역의 디지털 신호를 아날로그 전기신호로 변환시켜 출력하는 흡음 제어기; 흡음 제어기로부터 출력되는 전기신호를 증폭시키기 위한 신호 증폭기; 및 신호 증폭기에 의해 증폭된 전기신호를 입력받아 전기신호의 크기에 비례하는 소리신호를 잔향실 내로 출력하는 스피커를 포함한다.
잔향실, 흡음, 소리, 능동-
公开(公告)号：KR100530108B1
公开(公告)日：2005-11-22
申请号：KR1020030082301
申请日：2003-11-19
Applicant: 한국항공우주연구원
IPC: G10K15/04
Abstract: 본 발명은 기체의 압력 및 회전판을 이용한 소음신호 발생장치에 관한 것이다.
특히, 중공상의 실린더 내측으로 고속으로 회전하는 회전샤프트가 인입 연장 형성되고, 상기 실린더의 일단에서 지지플레이트가 회전샤프트를 지지하고, 복수개의 관통홀이 형성되는 고정플레이트가 상기 실린더의 타단에 고정 설치되고, 관통홀에 대응토록 소음홀이 복수개 형성되는 회전플레이트가 상기 회전샤프트의 단부에 고정 설치되며, 다수의 지지브라켓을 통해 베이스플레이트가 상기 실린더와 구동모터를 지지하는 구성으로 이루어 진다.
이에따라, 간단한 구조를 통한 소음신호의 주파수 변화가 가능하여 적은 비용으로도 인공위성체나 발사체에 발사에 있어 필수적인 소음 환경시험을 용이하게 수행할 수 있도록 하는 소음신호 발생장치를 제공한다.-
公开(公告)号：KR100372813B1
公开(公告)日：2003-02-25
申请号：KR1020000064596
申请日：2000-11-01
Applicant: 한국항공우주연구원
IPC: G01G23/00
Abstract: PURPOSE: A device for measuring mass property with adjustable slant is provided to measure mass property using a miniature reproduction of an attachment and a test object needed for mass property measurement test of a structure hard to directly test. CONSTITUTION: A device comprises a linear sliding rest(3); a moving rest(4); and a bracket(5). The linear sliding rest is installed on an upper side of a bottom plate(2) installed on a turn table(1). The moving rest moves and adjusts the center of gravity by a guide rest(3') connected with the linear sliding rest and has a rotary shaft(6) and a connective shaft(7) installed on both sides thereof. The bracket is connected with the rotary shaft and the connective shaft of the moving rest and has screw axes(11) protruding on four corners thereof to be connected with a clamp(12) above and a handle(13) fixing a missile(14).
Abstract translation: 目的：提供一种用于测量具有可调倾斜度的质量特性的装置，以便通过对难以直接测试的结构的质量特性测量测试所需的附件和测试对象的微型再现来测量质量特性。 组成：一种装置包括一个线性滑动架（3）; 移动的休息（4）; 和支架（5）。 线性滑动架安装在安装在转台（1）上的底板（2）的上侧。 移动架通过与直线滑架连接的导向架（3'）移动并调节重心，并在其两侧安装有旋转轴（6）和连接轴（7）。 支架与可动支架的旋转轴和连接轴连接，并在其四个角上突出有与上面的夹具（12）连接的螺旋轴（11）和固定导弹（14）的手柄（13） 。
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公开(公告)号：KR1020010056399A
公开(公告)日：2001-07-04
申请号：KR1019990057852
申请日：1999-12-15
Applicant: 한국항공우주연구원
IPC: G01N3/30
Abstract: PURPOSE: A shock tester is provided to selectively perform a direct shock test or an indirect shock test with one shock tester, thereby resolving troblesomeness and economical problem. CONSTITUTION: In a shock tester measuring numerical value of shock by falling a test piece fixing block(2) in which a test piece(3) is fixed and absorbing shock between impact tips(4,5) in the test piece(3), the shock tester includes a force transducer(10) detachably attached to the upper impact tip and obtaining shock degree to enable a direct shock test, and a fixing element(20) detachably attached to the lower impact tip to fix the test piece.
Abstract translation: 目的：提供一个冲击试验机，用一台冲击试验机选择性进行直接冲击试验或间接冲击试验，从而解决麻烦和经济问题。 规定：在冲击试验仪中，通过下降试验片固定块（2），测试试件（3）固定并吸收试件（3）的冲击尖端（4,5）之间的冲击，测量冲击的数值， 冲击试验机包括可拆卸地附接到上冲击尖端的力传感器（10）并且获得冲击度以实现直接冲击试验，以及可拆卸地附接到下冲击尖端以固定试件的固定元件（20）。
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公开(公告)号：KR1020000067381A
公开(公告)日：2000-11-15
申请号：KR1019990015140
申请日：1999-04-28
Applicant: 한국항공우주연구원
IPC: G01H17/00
Abstract: PURPOSE: A testing apparatus for a nuclear fuel rod supporting movement and vibration characteristic analysis is provided to prolong the life of the nuclear fuel rod by inspecting the vibration characteristic of supporting lattice members under the circumstances like actual circumstance. CONSTITUTION: A testing apparatus for a nuclear fuel rod supporting movement and vibration characteristic analysis includes a water tank(1) having a fixture(2) installed in the bottom in length direction, a plurality of heaters(5) installed in the side of the water tank, a plurality of supporting lattice members(3) fixed on the fixture for supporting the nuclear fuel rod, an exciting element(10) for impacting the nuclear fuel rod supported by the supporting lattice members, a laser displacement meter(20) measuring the displacement of the nuclear fuel rod, an accelerometer(7) held in the nuclear fuel rod, and a controller controlling the temperature of the water tank and receiving the measured data.
Abstract translation: 目的：提供一种核燃料棒支撑运动和振动特性分析的试验装置，通过在实际情况下检查支撑晶格构件的振动特性，延长核燃料棒的使用寿命。 构成：用于核燃料棒支撑运动和振动特性分析的测试装置包括：具有安装在底部长度方向上的固定装置（2）的水箱（1），多个加热器（5）安装在 水箱，固定在用于支撑核燃料棒的固定装置上的多个支撑格栅构件（3），用于冲击由支撑格架构件支撑的核燃料棒的激励元件（10），测量 核燃料棒的位移，保持在核燃料棒中的加速度计（7）和控制水箱的温度并接收测量数据的控制器。
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