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

Inventor： 최석원 ,  최준민 ,  류장수

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。

公开(公告)号：KR100298650B1

公开(公告)日：2001-09-22

申请号：KR1019980062610

申请日：1998-12-30

Applicant: 한국항공우주연구원

Inventor： 류장수 ,  이주진 ,  최종연 ,  윤용식

IPC: B64G1/22

Abstract: 본 발명은 위성체에 설치된 위성체 자세제어 센서 및 광학센서의 설치방향성을 측정하는 위성체 얼라인먼트 시스템 및 측정방법에 관한 것이다.
이러한 본 발명은 데오도라이트, 자동수평측정계, 회전테이블을 데이타 전송선으로 데이타처리 시스템과 연결시킨 상태에서 위성체가 설치된 회전테이블을 회전시켜 센서에 부착된 표적(Target Mirror)를 데오도라이트와 오토클리메이션(Autocollimation)하고, 데오도라이트를 회전하여 반사경에 다시 오토콜리메이션한 후 데오도라이트와 회전테이블에서 측정된 회전각을 이용하여 데이타처리시스템에서 목표의 방향성을 측정하도록 하므로써 이루어진다.

公开(公告)号：KR1020010058829A

公开(公告)日：2001-07-06

申请号：KR1019990066200

申请日：1999-12-30

Applicant: 한국항공우주연구원

Inventor： 최석원 ,  최준민 ,  류장수

IPC: F16K17/00

Abstract: PURPOSE: A safety valve is provided to remove cooling water or actuating fluid remaining inside a pipe in case of equipment stop for preventing breakage from cold and to remove residues. CONSTITUTION: In a rear end of an electronic valve(12), a one-way valve(13) is installed and an actuating fluid running along a T-shaped valve(5) is not allowed toward the electronic valve while only high pressure gas that has passed through the electronic valve is allowed to pass through the one-way valve. When power is normally supplied, a normal cross typed electronic valve(11) is open and the normal open typed electronic valve is closed causing the actuating fluid introduced in an actuating fluid inlet port(6) to be normally let in a pipe(7) for normal action. In case of work finished or emergency, power supply is stopped then the normal cross typed electronic valve(11) is intercepted to stop introduction of the actuating fluid. Instead, the normal open typed electronic valve is open for high pressure gas to be introduced into the pipe. Thereby, the actuating fluid remaining in the pipe is completely removed inside the pipe and danger of breakage or a problem of residues disappears.

Abstract translation: 目的：提供一个安全阀，用于在设备停止时防止冷却水或导管内残留的流体，以防止发生冷冻和去除残留物。 构成：在电子阀（12）的后端安装有单向阀（13），并且不允许沿着T形阀（5）运行的致动流体朝向电子阀，而只有高压气体 允许通过电子阀的单向阀通过。 当正常供电时，正常的交叉型电子阀（11）打开，并且常开型电子阀关闭，导致引入到致动流体入口（6）中的致动流体通常被放入管（7）中， 为正常行动。 在工作完成或紧急情况下，电源停止，则正常交叉型电子阀（11）被截断以停止引导致动流体。 相反，普通开式电子阀是开放的，用于高压气体被引入到管道中。 因此，保持在管道中的致动流体在管道内被完全去除，并且具有断裂的危险或残留物的问题消失。

公开(公告)号：KR1019990085579A

公开(公告)日：1999-12-06

申请号：KR1019980018075

申请日：1998-05-20

Applicant: 한국항공우주연구원

Inventor： 최석원 ,  최준민 ,  류장수

IPC: B64G7/00

Abstract: 본 발명은 지상에서 우주환경을 모사하는 열진공 챔버에 관한 것으로, 위성체의 크기에 따라 신축적으로 챔버의 크기를 확장시킬 수 있는 확장형 열진공 챔버에 관한 것이다.
이러한 본 발명은 몸통챔버에서 도어가 분리되는 도어 개방형 열진공 챔버에 있어서, 원통형으로 이루어지고 몸통챔버와 직경이 동일한 확장챔버와, 확장챔버의 양측면과 몸통챔버 및 도어 사이의 밀봉고정을 위한 고정수단과, 확장챔버를 몸통챔버의 전면으로 이동시키는 이동수단을 구비시킴으로써 이루어진다.

公开(公告)号：KR100267025B1

公开(公告)日：2000-10-02

申请号：KR1019980018075

申请日：1998-05-20

Applicant: 한국항공우주연구원

Inventor： 최석원 ,  최준민 ,  류장수

IPC: B64G7/00

Abstract: PURPOSE: An expansion type thermal vacuum chamber is provided to flexibly expand a size of the chamber depending on a size of a satellite body. CONSTITUTION: A door(2) is completely separated from a body chamber(1) and is supported by a lower roller to move over a rail. An expansive chamber(10) has rollers downstream to move left and right directions over rails(13,13') and the rollers are combined in a screw method to the expansive chamber. Thus upon demand, height adjustment of the expansive chamber is available by rotation of a screw. In a top of the expansive chamber, a ring(12) is fixed to easily move with a crane. A fixing instrument sealing the expansive chamber to the body chamber includes an O ring at both faces of the body chamber and at the expansive chamber. In case a diameter of the expansive chamber is enlarged, the O rings are fixed doubly between the body chamber and the expansive chamber(10) and between the O rings, a groove is formed. Therefore, by attaching the expansive chamber to the thermal vacuum chamber, the thermal vacuum chamber is used by expanding and also adapted for other satellite tests.

Abstract translation: 目的：提供一种膨胀型热真空室，以根据卫星体的大小灵活扩大腔室的尺寸。 构成：门（2）与主体室（1）完全分离，并由下辊支撑以在轨道上移动。 膨胀室（10）具有下游的辊子，以使轨道（13,13'）上的左右方向移动，并且将滚轮以螺杆方式组合到膨胀室。 因此，根据需要，通过旋转螺杆可获得膨胀室的高度调节。 在膨胀室的顶部，固定环（12）以容易地用起重机移动。 将膨胀室密封到身体腔室的固定器具包括在主体腔室的两个表面和膨胀室的O形环。 在膨胀室的直径扩大的情况下，O形环在体腔和膨胀室（10）之间以及O形环之间双重固定，形成凹槽。 因此，通过将膨胀室连接到热真空室，通过膨胀使用热真空室，并适用于其他卫星测试。

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

Inventor： 최석원 ,  최준민 ,  류장수

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：KR100318279B1

公开(公告)日：2001-12-24

申请号：KR1019990066200

申请日：1999-12-30

Applicant: 한국항공우주연구원

Inventor： 최석원 ,  최준민 ,  류장수

IPC: F16K17/00

Abstract: 본발명은냉각수또는작동유체를사용하는장비에서배관내의냉각수또는작동유체를완전히제거해주도록하는안전밸브에관한것이다. 이러한본 발명은작동유체유입구와배관사이에 T자형밸브를설치하여작동유체가 T자형밸브를통하여배관으로유입되게하고, T자형밸브의잔여입구에는고압가스배관을연결하며, 상기작동유체유입구쪽밸브에는노말크로스형전자밸브를설치하고고압가스배관쪽밸브에는노말오픈형전자밸브를설치하므로써이루어진다.

公开(公告)号：KR1020000045961A

公开(公告)日：2000-07-25

申请号：KR1019980062611

申请日：1998-12-30

Applicant: 한국항공우주연구원

Inventor： 문상무 ,  이진호 ,  천용식 ,  류장수

IPC: H04B17/00

CPC classification number: H04W24/06 ,  G01S19/23 ,  H04B17/21

Abstract: PURPOSE: A ground test equipment for a satellite GPS receiver is provided to test a GPS receiver easily at a satellite test facility located on the ground. CONSTITUTION: A GPS satellite signal from an exterior antenna is inputted to an input port(1). A channel simulator signal to simulate the GPS satellite signal is inputted to an input port(2). A switch element(20) selects one out of the signals inputted to the input ports(1,2) alternatively. A first divider(30) divides the signal selected at the switch element(20) into 4 outputs. The 3 outputs are connected to a satellite receiver through each output port(3-5). An amplifier(50) amplifies one signal outputted from the first divider(30). A second divider(70) divides the signal amplified in the amplifier(50) into 4 outputs. The 4 outputs are transferred to the satellite receiver through each output port(6-9) respectively.

Abstract translation: 目的：提供用于卫星GPS接收机的地面测试设备，用于在位于地面的卫星测试设备上轻松测试GPS接收机。 构成：将来自外部天线的GPS卫星信号输入到输入端口（1）。 将模拟GPS卫星信号的信道模拟器信号输入到输入端口（2）。 开关元件（20）交替地选择输入到输入端口（1,2）的信号中的一个。 第一分频器（30）将在开关元件（20）处选择的信号分成4个输出。 3个输出端通过每个输出端口连接到卫星接收机（3-5）。 放大器（50）放大从第一分频器（30）输出的一个信号。 第二分频器（70）将放大器（50）中放大的信号分成4个输出。 4个输出分别通过每个输出端口（6-9）传输到卫星接收机。

公开(公告)号：KR1020000045960A

公开(公告)日：2000-07-25

申请号：KR1019980062610

申请日：1998-12-30

Applicant: 한국항공우주연구원

Inventor： 류장수 ,  이주진 ,  최종연 ,  윤용식

IPC: B64G1/22

Abstract: PURPOSE: A satellite alignment system and method for measuring a setting orientation is provided to measure the setting orientation of a sensor for controlling the attitude of a satellite body and an optical sensor. CONSTITUTION: In a satellite alignment system and method for measuring the setting orientation, the satellite alignment system comprises a seismic mass(10), a vertical tooling bar(20), a theodolite(30), a rotating table(40), an azimuth prism(50), an automatic inclinometer(60), and a data acquisition system(70). In the method for measuring a setting orientation, an auto collimation between target mirrors attached to sensors and a theodolite(30) is carried out by rotating a rotating table(40) on which a satellite body is mounted under the state of connecting the theodolite(30), an automatic inclinometer(60), and the rotating table(40) to a data acquisition system(70) with a data transferring cable. Then, after an auto collimation against the azimuth prism(50) is carried out again by rotating the theodolite(30), measuring of an orientation of a target is performed in the data acquisition system(70) by using a rotating angle measured in the theodolite(30) and the rotating table(40).

Abstract translation: 目的：提供用于测量设置方向的卫星对准系统和方法，以测量用于控制卫星体和光学传感器姿态的传感器的设置方向。 构成：在卫星对准系统和测量设定方向的方法中，卫星对准系统包括地震块（10），垂直工具杆（20），经纬仪（30），旋转台（40），方位角 棱镜（50），自动倾斜计（60）和数据采集系统（70）。 在用于测量设定方向的方法中，通过在连接经纬仪的状态下旋转安装有卫星体的旋转台（40）来实现附接到传感器的目标反射镜和经纬仪（30）之间的自动准直（ 30），自动倾斜计（60）和旋转台（40）连接到具有数据传送电缆的数据采集系统（70）。 然后，在通过旋转经纬仪（30）再次进行对方位角棱镜（50）的自动准直之后，通过使用在数据采集系统（70）中测量的旋转角度，在数据采集系统（70）中进行目标的取向的测量 经纬仪（30）和旋转台（40）。

公开(公告)号：KR100334511B1

公开(公告)日：2002-04-26

申请号：KR1019990031138

申请日：1999-07-29

Applicant: 한국항공우주연구원

Inventor： 류장수 ,  천용식 ,  조창범

IPC: G01M99/00

Abstract: 본발명은우주공간에서인공위성의자세제어를위해사용되는센서중의하나로적외선을이용하는원추지구센서(Conical Earth Sensor: 이하 CES라칭함)의기능을지상에서시험할수 있도록적외선센서시험장치에관한것이다. 이러한본 발명은인공위성에조립된 CES의전방에서적외선을발생시키는열선이장착된반응판을구비하고, 상기반응판에공급되는전압과전류를제어하는파우어서플라이를구비하며, 상기파우어서플라이를제어하여반응판에서발생하는적외선의량을제어하는컴퓨터를구비시킴으로써이루어지는것이다.