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公开(公告)号：KR1019990085581A
公开(公告)日：1999-12-06
申请号：KR1019980018077
申请日：1998-05-20
Applicant: 한국항공우주연구원
IPC: B64G7/00
Abstract: 본 발명은 지상에서 우주환경을 모사하는 열진공 챔버에서, 독립식 히터판을 설치하여 저렴한 비용으로 태양광을 포함한 우주환경을 간단히 모사시키도록 하는 히터판을 이용한 열진공 챔버에 관한 것이다.
이러한 본 발명은 슈라우드가 내장된 열진공 챔버에 있어서, 위성체의 바깥쪽에 알루미늄판을 수직으로 설치하되 상기 알루미늄판에는 와이어 히터를 위성체쪽으로 배열한 후 알루미늄 테이프로 부착하여 알루미늄판과 위성체의 태양광 조사면사이에 독립적으로 복사열전달이 이루어지도록 설치하므로써 이루어진다.-
公开(公告)号：KR1020090066821A
公开(公告)日：2009-06-24
申请号：KR1020070134526
申请日：2007-12-20
Applicant: 한국항공우주연구원
Abstract: A fixation apparatus of reflector for laser tracer is provided to prevent the variation of vibration and position of reflector. A fixation apparatus of reflector for laser tracer comprises a bolt groove insertion unit, reflector support. The bolt groove insertion unit(10) is inserted to the bolt groove. The reflector support unit(20) supports the reflector and is connected to the bolt groove insertion unit. The reflector support unit comprises a groove, and supporting surface.
Abstract translation: 提供用于激光跟踪器的反射器的固定装置，以防止反射器的振动和位置的变化。 用于激光跟踪器的反射器的固定装置包括螺栓槽插入单元，反射器支撑件。 螺栓槽插入单元（10）插入到螺栓槽中。 反射器支撑单元（20）支撑反射器并连接到螺栓槽插入单元。 反射器支撑单元包括凹槽和支撑表面。
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13.发明授权보오크사이트를 이용한 고강도 특성을 지닌 우주비행체추력기용 하이드라진 분해용 이리듐 촉매의 제조방법 및그로부터 수득되는 이리듐 촉매 有权一种利用铝土矿和铱催化剂制备具有高强度特性的航天器推进器用于肼分解的铱催化剂的方法
公开(公告)号：KR100712637B1
公开(公告)日：2007-04-30
申请号：KR1020050128682
申请日：2005-12-23
Applicant: 한국항공우주연구원
Abstract: 본 발명은 산처리 및 열처리를 수행하여 고온에서 고강도 특성을 나타낼 수 있도록 한, 우주비행체 추력기용 하이드라진 분해용 이리듐 촉매의 제조방법에 관한 것으로서, (1) 보오크사이트를 0.1 내지 10M의 농도의 산과 10 내지 14시간 동안 접촉시키는 산처리단계; (2) 상기 산처리단계 후, 고형분으로서의 보오크사이트를 상기 산으로부터 여과해내는 여과단계; (3) 상기 산처리된 보오크사이트를 500 내지 700℃의 온도범위의 열풍과 2 내지 6시간 동안 접촉시키는 열처리단계; (4) 상기 열처리된 보오크사이트에 촉매로서의 이리듐을 담지시키는 촉매담지단계; 및 (5) 상기 촉매담지된 보오크사이트의 촉매를 환원시키는 환원단계;들을 포함하여 이루어짐을 특징으로 한다.
우주비행체, 하이드라진 추력기, 이리듐 촉매, 담체, 침전 알루미나, 보오크사이트Abstract translation: 本发明涉及一种制造，空间飞行器肼铱催化剂为推进器通过进行酸处理和热处理0.1表现出在高温下的高强度特性，（1）酸和橡木部位的束密度的至10M的方法 10至14小时; （2）在酸处理步骤之后，过滤来自酸的作为固体组分的勃姆石的过滤步骤; （3）使酸处理过的铝土矿与温度为500-700℃的热空气接触2至6小时的热处理步骤; （4）在热处理过的铝土矿上负载铱作为催化剂的催化剂负载步骤; （5）还原催化剂负载铝土矿的催化剂的还原步骤。
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公开(公告)号：KR100542037B1
公开(公告)日：2006-01-12
申请号：KR1020030090212
申请日：2003-12-11
Applicant: 한국항공우주연구원
IPC: G06F11/273
Abstract: 본 발명은 프로세서(컴퓨터)에 의해 조절되는 히터 회로의 논리를 검증하고 실제 작동온도를 확인 가능하게 하는 프로세서에 의해 작동되는 히터 회로의 논리를 검증하기 위한 시험방법 및 그 장치에 관한 것이다.
이러한 본 발명은 알루미늄의 금속판에 히터를 설치하고 그 일측으로 프로세서와 연결된 온도센서, 독립적으로 온도가 기록되는 열전대를 서로 가까이 설치한 히터판에 쿨링 스프레이를 이용하여 프로세서에 의해 작동하는 히터 회로를 검증 시험함을 특징으로 하는 프로세서에 의해 작동되는 히터 회로의 논리를 검증하기 위한 시험방법과, 내부에 단열효과가 좋은 재질로 히터판이 설치되는 다수의 홈이 내측으로 형성된 작업대, 작업대의 양측에서 지면과 30도 정도의 경사를 갖도록 유지하도록 접힘식으로 설치되는 받침대로 이루어지는 장치로 구성된다.
알루미늄 히터판, 작업대, 프로세서, 히터회로-
公开(公告)号：KR1020050002760A
公开(公告)日：2005-01-10
申请号：KR1020040105968
申请日：2004-12-15
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An earth environment test apparatus having a dynamic test simulation function of a conical earth sensor is provided to easily perform an earth environment test by heating a desired part of a heating plate without changing a position of the earth environment test apparatus. CONSTITUTION: An earth environment test apparatus having a dynamic test simulation function of a conical earth sensor includes a plurality of heating plates(1) aligned in a matrix pattern. A heater is provided to heat the heating plate(1). A power supply is connected to each heating plate(1). A controller is provided to control each power supply in order to adjust a temperature of each heating plate(1). Each heating plate is sequentially heated by the controller. The heating plate(1) is connected to a supporting rod(2), and the supporting rod(2) is installed at a front surface of the conical earth sensor through a bracket(3).
Abstract translation: 目的：提供一种具有锥形接地传感器的动态试验模拟功能的地球环境试验装置，通过在不改变地球环境试验装置的位置的情况下加热加热板的所需部分来容易地进行地球环境试验。 构成：具有锥形接地传感器的动态试验模拟功能的地球环境试验装置包括以矩阵状排列的多个加热板（1）。 提供加热器以加热加热板（1）。 电源连接到每个加热板（1）。 提供控制器来控制每个电源以便调节每个加热板（1）的温度。 每个加热板由控制器依次加热。 加热板（1）连接到支撑杆（2），支撑杆（2）通过托架（3）安装在锥形接地传感器的前表面。
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Patent Agency Ranking
公开(公告)号：KR1020010065118A
公开(公告)日：2001-07-11
申请号：KR1019990064932
申请日：1999-12-29
Applicant: 한국항공우주연구원
IPC: G01K7/00
Abstract: PURPOSE: A temperature sensor setting method for a vacuum chamber is provided to easily control a temperature in a vacuum chamber by setting a representative temperature in spite of mounting an electric heater directly in the chamber. CONSTITUTION: A temperature sensor setting method for a vacuum chamber includes the steps of deducting a temperature value sensed by a second temperature sensor(7) mounted in the center of an upper part of a heater(3) of a thermal vacuum chamber(1) from an internal temperature of the thermal vacuum chamber, adding a previous temperature value sensed by a first temperature sensor(6) mounted in front of the heater of the thermal vacuum chamber to the deduction value, and changing a setting value of the first temperature sensor by the add value.
Abstract translation: 目的：提供一种用于真空室的温度传感器设置方法，以便通过设置代表性温度来容易地控制真空室中的温度，尽管将电加热器直接安装在室中。 构成：真空室的温度传感器设定方法包括以下步骤：扣除由安装在热真空室（1）的加热器（3）的上部中心的第二温度传感器（7）感测到的温度值， 从所述热真空室的内部温度，将安装在所述热真空室的所述加热器前面的第一温度传感器（6）感测到的先前温度值加到所述减除值上，并且改变所述第一温度传感器 通过附加值。
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公开(公告)号：KR100267023B1
公开(公告)日：2000-10-02
申请号：KR1019980018077
申请日：1998-05-20
Applicant: 한국항공우주연구원
IPC: B64G7/00
Abstract: PURPOSE: A thermal vacuum chamber is provided to enable radiant heat delivery independently from a wire heater and to achieve a radiant heat delivery with a chamber shroud in a portion that does not receive solar beam. CONSTITUTION: In a side of an aluminum plate(20), a wire heater(21) is arranged and at a rear of the aluminum plate, a teflon plate(30) is attached to form a heating plate(10). A shroud of the thermal vacuum chamber is kept to be a cryogenic temperature and the heating plate is installed outward of a satellite body(40). On the aluminum plate(20) of the heater plate, a black paint is painted to create a big radiant rate and the wire heater(21) is adapted with an aluminum tape to perform a big heat conductivity. At a portion where the satellite body(40) is predicted to be irradiated by a sunlight and at each side, a multi-story-insulating curtain(60) is installed and a desired portion of the satellite is designed to view only the heater plate(10) to deliver radiant heat independently from other heaters.
Abstract translation: 目的：提供一个热真空室，以独立于电线加热器实现辐射热传递，并实现辐射热传递，其中室护罩处于不接收太阳能束的部分。 构成：在铝板（20）的一侧，设置线加热器（21），并且在铝板的后部安装有特氟龙板（30）以形成加热板（10）。 热真空室的护罩保持为低温温度，并且加热板安装在卫星体（40）的外部。 在加热器板的铝板（20）上，涂上黑色涂料以产生大的辐射率，并且电线加热器（21）适合于铝带以实现大的导热性。 在预测卫星体（40）被太阳光照射的部分处，并且在每一侧安装有多层隔热幕（60），卫星的所需部分被设计成仅观察加热板 （10）独立于其他加热器传递辐射热。
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公开(公告)号：KR1020180052274A
公开(公告)日：2018-05-18
申请号：KR1020160149407
申请日：2016-11-10
Applicant: 한국항공우주연구원
Inventor： 최준민
CPC classification number: 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
Abstract: 일실시예에따른우주쓰레기제거용위성은, 위성본체; 상기위성본체의외측면에접힘가능하고, 우주쓰레기를향하여배치되어상기우주쓰레기의이동속도를감소시키는방패부재; 및상기위성본체에대하여상기방패부재를지지하는지지부재;를포함하고, 상기방패부재는, 상기위성본체의일면에겹쳐지는중앙패널; 상기중앙패널의측면에연결되어, 방사상방향으로연장되는복수개의제1 패널; 및상기복수개의제1 패널사이에연결된복수개의제2 패널;을포함할수 있다.
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公开(公告)号：KR100681481B1
公开(公告)日：2007-02-09
申请号：KR1020050119452
申请日：2005-12-08
Applicant: 한국항공우주연구원
Abstract: An apparatus for measuring performance of an iridium catalyst is provided to be able to prevent enormous expense incurred by performance lowering of the catalyst, and delay of the schedule through the performance measurement of the iridium catalyst according to simple principle, thereby smoothly performing the development of artificial satellite. The apparatus for measuring performance of an iridium catalyst comprises: a propellant pressurizing portion(100) controlling a highly pressured pressurizing agent(1) of an inert gas which is emitted by controlling a plurality of valves within a certain range of pressure so as to discharge the pressurizing agent and including a pressurizing agent supplying valve(2), a pressure control valve for high pressure(4) and a pressure control for low pressure(6); a propellant supplying portion(200) applying the pressurizing agent input from the propellant pressurizing portion into a propellant(11) stored in a certain space to discharge the propellant according to the input pressurizing agent to supply the propellant and including a supply tank(12), a discharge tank(17), and a vapor discharge tank(10); a catalyst reaction portion(300) which controls the propellant input from the propellant supplying portion to a predetermined temperature, prevents rapid pressure change thereof and then sprays it to an iridium catalyst(25) placed at a reaction facility to allow the reaction thereof and includes a water jacket(20), a circulator(21), an orifice(22), a solenoid valve(23), a reactor(26), and an electric heater(24); and a test measurement portion(400) which controls the supply of the propellant input from the catalyst reaction portion and analyzes transmitted signals detected from a plurality of sensors installed at the surrounding of the catalyst reaction portion and includes a D/A converter(30), an A/D converter(32) and a computer(31).
Abstract translation: 提供了一种用于测量铱催化剂性能的设备，以便能够通过根据简单原理通过铱催化剂的性能测量来防止由于催化剂性能下降而导致的巨大费用，以及延迟计划，从而顺利地进行 卫星。 用于测量铱催化剂性能的设备包括：推进剂加压部分（100），用于控制通过在一定压力范围内控制多个阀而排放的惰性气体的高压加压剂（1），以排出 （2），用于高压（4）的压力控制阀和用于低压（6）的压力控制器，所述加压剂包括加压剂供给阀（2）。 推进剂供给部分，将从推进剂加压部分输入的加压剂输入到存储在特定空间中的推进剂中，以根据输入的加压剂排出推进剂以供给推进剂并且包括供给箱; ，排放罐（17）和蒸汽排放罐（10）; 控制从推进剂供给部分的推进剂输入到预定温度的催化剂反应部分（300）防止其快速压力变化，然后将其喷射到放置在反应设施处的铱催化剂（25）以允许其反应并包括 水套（20），循环器（21），节流孔（22），电磁阀（23），反应器（26）和电加热器（24）。 和控制从催化剂反应部分输入的推进剂的供给并分析从安装在催化剂反应部分的周围的多个传感器检测到的传送信号的测试测量部分（400），并包括D / A转换器（30） ，A / D转换器（32）和计算机（31）。
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公开(公告)号：KR100647207B1
公开(公告)日：2006-11-23
申请号：KR1020050129462
申请日：2005-12-26
Applicant: 한국항공우주연구원
Abstract: A satellite workbench for fixing a paddle is provided to restrict turning moment, to work stably and safely, and to improve working efficiency by simply mounting and detaching the paddle from a lower part of the satellite workbench. A satellite workbench(200) includes a workbench body(210) having a paddle fixing bar(211) with a fixing support unit(211a) to fix and support a paddle(220) in a lower part of a body, and the paddle thread-connected to the pad fixing bar, extended in a lower part of the workbench body and provided with a support unit(222) supporting a worker. The satellite workbench for fixing the paddle is moved into a satellite without being contacted to the satellite to improve safety in working. The paddle is placed in the paddle fixing bar in not fastening the paddle to the paddle fixing bar.
Abstract translation: 提供用于固定桨的卫星工作台以限制转动力矩，从而稳定和安全地工作，并且通过简单地将卫生间从卫星工作台的下部安装和拆卸来提高工作效率。 卫星工作台（200）包括工作台本体（210），该工作台本体（210）具有带固定支撑单元（211a）的桨固定杆（211）以将桨（220）固定并支撑在本体的下部中，并且桨叶线 连接到所述垫固定杆，延伸到所述工作台本体的下部并且设置有支撑工人的支撑单元（222）。 用于固定桨的卫星工作台被移入卫星而不与卫星接触以提高工作的安全性。 将桨叶放在桨叶固定杆中，而不将桨叶固定到桨叶固定杆上。
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