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公开(公告)号：KR100778098B1
公开(公告)日：2007-11-22
申请号：KR1020060070263
申请日：2006-07-26
Applicant: 한국항공우주연구원
IPC: G05D1/08
CPC classification number: G05D1/0883
Abstract: A moment gyro cluster for three axis attitude control of an artificial satellite is provided to improve torque performance by using an MPP(Moore-Penrose Pseudoinverse) driving law. A moment gyro cluster is mounted with a predetermined rotation angle(sigma) between 0° and 360°. Sequential torque inputs are applied as much as rotation amounts of an artificial satellite along an axis direction using a new pyramid shape which the moment gyro cluster is mounted with the predetermined rotation angle. Torque inputs corresponding to x, y, and z axes are sequentially applied in accordance with an artificial satellite attitude movement range in respective axes such that an artificial satellite attitude movement is performed.
Abstract translation: 提供用于人造卫星的三轴姿态控制的力矩陀螺集群，以通过使用MPP（Moore-Penrose伪逆）驱动规律来提高扭矩性能。 一个陀螺仪簇以0°至360°之间的预定旋转角度（sigma）安装。 使用以预定旋转角度安装力矩陀螺集群的新的金字塔形状，沿轴向方向施加顺序扭矩输入多达人造卫星的旋转量。 按照各轴的人造卫星姿态移动范围依次施加对应于x，y，z轴的转矩输入，从而进行人造卫星姿态移动。
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公开(公告)号：KR100766000B1
公开(公告)日：2007-10-12
申请号：KR1020060128495
申请日：2006-12-15
Applicant: 한국항공우주연구원
IPC: B64G1/24
CPC classification number: B64G1/36 , G05D1/0883
Abstract: An integrated verification system for controlling a satellite attitude is provided to improve the efficiency of control logic verification by displaying a geometric appearance of a satellite in a three-dimensional space. An integrated verification system comprises a satellite dynamic simulator(10), a remote interface device(20), an embedded computer simulator(30), a satellite attitude control three-dimensional graphic visual device(40), a star simulator(50) and a host PC(60). The satellite dynamic simulator(10) includes a hardware having a commercial board and a custom board, and a software. The remote interface device(20) collects information on satellite attitude from an attitude control sensor, and sends the information to an attitude control logic.
Abstract translation: 提供用于控制卫星姿态的综合验证系统，以通过在三维空间中显示卫星的几何外观来提高控制逻辑验证的效率。 集成验证系统包括卫星动态模拟器（10），远程接口设备（20），嵌入式计算机模拟器（30），卫星姿态控制三维图形视觉设备（40），星型模拟器（50）和 主机PC（60）。 卫星动态模拟器（10）包括具有商业板和定制板的硬件以及软件。 远程接口装置（20）从姿态控制传感器收集关于卫星姿态的信息，并将该信息发送到姿态控制逻辑。
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公开(公告)号：KR100649730B1
公开(公告)日：2006-11-27
申请号：KR1020050129700
申请日：2005-12-26
Applicant: 한국항공우주연구원
IPC: G01C19/56
Abstract: A control moment gyroscope is provided to mount a gimbal motor to a lower portion of one side of a wheel rotated by a spin motor, thereby controlling the posture of a small-sized satellite. A control moment gyroscope includes a spin motor(200), a spin shaft(220), a wheel(210), a gimbal motor(100), a lower connection shaft(120), an upper connection shaft(130), and a sensing section(110). The gimbal motor is disposed at a lower portion of the lower side of the wheel and supplies a moment perpendicular to the rotation direction of the spin motor. The lower connection shaft is mounted to the gimbal motor to rotate the wheel mounted to the spin motor. The upper connection shaft penetrates from the spin motor and extends upward. The sensing section accommodates the upper connection shaft.
Abstract translation: 提供控制力矩陀螺仪以将万向电机安装到由旋转电机旋转的车轮的一侧的下部，从而控制小尺寸卫星的姿态。 控制力矩陀螺仪包括旋转电机200，旋转轴220，轮210，万向电机100，下连接轴120，上连接轴130， 感测部分（110）。 万向电机设置在车轮下侧的下部，并提供垂直于旋转电机旋转方向的力矩。 下连接轴安装在万向节马达上，以旋转安装在旋转马达上的轮子。 上连接轴从旋转电机穿入并向上延伸。 传感部分容纳上连接轴。
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公开(公告)号：KR100533192B1
公开(公告)日：2005-12-05
申请号：KR1020030075764
申请日：2003-10-29
Applicant: 한국항공우주연구원
IPC: B64G1/24
Abstract: 본 발명은 연동 추력 방식을 사용하는 위성의 변분사비율 추력 제어방법에 관한 것으로, 상세하게는 위성의 궤도 조절과 자세제어에 사용되는 추력기를 장착한 위성 중 추력기의 수가 적어 연동식으로 작동되어야 하는 추력기 세트를 장착한 위성의 추력분사비율 조정법중 가변 분사비율 방법을 제공하기 위함이다.
상기한 목적을 달성하기 위하여 본 발명은 임의의 순간 위성자세 제어를 위하여 각 축의 토크 분사비율( u
i ≡ t
i / t
s , i=1,2,3, t
i =분사시간, t
s =제어시간간격)을 하기 식과 같은 조건 u
1 + u
2 + u
3 ≤ 1 을 만족시키되 각축의 분사비율이 하기식과 같은 경우에 따라 1/3이 넘을 수 있도록 가변적으로 할당(Varying Time Division)하여
0 ≤ u
i ≤ 1, i=1,2,3
결과적으로 각축에 발생하는 상당토크 g
i 가 하기 식과 같이
g
i = g
i max u
i
가 되어 각 축에 발생되는 상당토크를 극대화시키는 방법을 제공하게 된다.(여기서 g
i max 는 i번째 축의 최대 발생가능 토크를 나타냄)-
公开(公告)号：KR100456908B1
公开(公告)日：2004-11-10
申请号：KR1020020073517
申请日：2002-11-25
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An apparatus and a method for calibration for a micro flow rate of an impulse-output type flowmeter are provided to precisely measure a micro flow rate of fluid by converting an impulse value into a value of the micro flow rate. CONSTITUTION: A flow rate calibration apparatus includes a fluid feeding tank, a static pressure calibration tank, an impulse-output type flowmeter, and an output signal processing unit. The fluid feeding tank stores fluid therein. When a flow rate valve(7) connected to a compensation tank(10) is opened, the fluid feeding tank feeds fluid into various components. The static pressure calibration tank includes the flow rate valve(7), a storage tank(10), a balance(17), a static pressure control valve(13), a flexible pipe(12), thermometers(14,16) and a pressure meter(15).
Abstract translation: 目的：提供一种用于脉冲输出型流量计的微流量校准的设备和方法，以通过将脉冲值转换为微流率值来精确测量流体的微流量。 构成：流量校准装置包括流体供给箱，静压校正箱，脉冲输出型流量计和输出信号处理单元。 流体供给罐在其中存储流体。 当连接到补偿罐（10）的流量阀（7）打开时，流体供给罐将流体供给到各种部件中。 静压校准罐包括流量阀（7），储罐（10），天平（17），静压控制阀（13），软管（12），温度计（14,16）和 压力计（15）。
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Patent Agency Ranking
公开(公告)号：KR100437512B1
公开(公告)日：2004-06-30
申请号：KR1020010080115
申请日：2001-12-17
Applicant: 한국항공우주연구원
IPC: F17D1/05
Abstract: PURPOSE: A breakage preventing device of the sealing of a CryoFit coupling in a very low temperature environment is provided to control the operation of a heater and to uniformly maintain the coupling over a certain temperature, the sealing and the connection of pipes by sticking a heater in the coupling and by adjusting a power supplier through a thermostat or a power controller. CONSTITUTION: A heater(1), a thermostat and a power supplier(4) are connected serially and controlled mechanically. The heater is connected with a power controller(5) through the power supplier and a temperature sensor(3) is connected with the power controller to control electronically. Thereby, the breakage of a sealing by an expansion of a CryoFit coupling in a very low temperature environment is prevented.
Abstract translation: 目的：提供一种在极低温度环境下密封CryoFit接头的防破裂装置，以控制加热器的操作并在一定温度下均匀地维持接头，通过粘接加热器来密封和连接管道 在耦合中以及通过恒温器或功率控制器调整电源供应器。 构成：加热器（1），恒温器和电源（4）串联连接并机械控制。 加热器通过电源与电源控制器（5）连接，温度传感器（3）与电源控制器连接，实现电子控制。 由此，防止了在非常低的温度环境下通过CryoFit接头的膨胀而造成的密封破损。
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公开(公告)号：KR1020030050317A
公开(公告)日：2003-06-25
申请号：KR1020010080730
申请日：2001-12-18
Applicant: 한국항공우주연구원
IPC: F16L13/14
CPC classification number: F16L13/147
Abstract: PURPOSE: A joining method of a pipe using a shape memory alloy coupling under a condition impossible to weld is provided to connect pipes easily and simply in a short time even under work conditions are impossible to weld. CONSTITUTION: In a joining method of a pipe using a shape memory alloy coupling(1) under a conditions impossible to weld, the surface and the ends of pipes(4,5) are smoothly trimmed and an installation position indication part(6) is indicated at a position of the surface of the pipe to install the shape memory alloy coupling, using a marking gauge. The shape memory alloy coupling maintained on a low expansion state is kept in an insulating box. The shape memory alloy coupling kept in the insulating box is inserted into the installation indication part of the pipe(5) and then the pipe(4) is inserted into the shape memory alloy coupling from the opposite side. Connection is fixed while the shape memory alloy coupling contracts.
Abstract translation: 目的：提供在不可焊接条件下使用形状记忆合金联轴器的管道的接合方法，即使在工作条件下也能够在短时间内容易地简单地连接管道，从而不可能焊接。 构成：在不能焊接的条件下使用形状记忆合金联轴器（1）的管道的接合方法中，管道（4,5）的表面和端部被平滑地修整，并且安装位置指示部分（6）是 表示在管的表面的位置，使用标记仪安装形状记忆合金联轴器。 保持在低膨胀状态的形状记忆合金耦合体保持在绝缘箱中。 将保存在绝缘箱中的形状记忆合金联轴器插入管（5）的安装指示部分，然后将管（4）从相对侧插入形状记忆合金联轴器。 形状记忆合金联轴器收缩时连接固定。
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公开(公告)号：KR1020030049798A
公开(公告)日：2003-06-25
申请号：KR1020010080115
申请日：2001-12-17
Applicant: 한국항공우주연구원
IPC: F17D1/05
Abstract: PURPOSE: A breakage preventing device of the sealing of a CryoFit coupling in a very low temperature environment is provided to control the operation of a heater and to uniformly maintain the coupling over a certain temperature, the sealing and the connection of pipes by sticking a heater in the coupling and by adjusting a power supplier through a thermostat or a power controller. CONSTITUTION: A heater(1), a thermostat and a power supplier(4) are connected serially and controlled mechanically. The heater is connected with a power controller(5) through the power supplier and a temperature sensor(3) is connected with the power controller to control electronically. Thereby, the breakage of a sealing by an expansion of a CryoFit coupling in a very low temperature environment is prevented.
Abstract translation: 目的：提供在非常低的温度环境下对CryoFit联轴器进行密封的防破裂装置，以控制加热器的操作，并在一定温度下均匀地保持联轴器，通过粘贴加热器来密封和连接管道 通过调节器或电源控制器调节电源。 构成：加热器（1），恒温器和电源（4）以机械方式连续和连续连接。 加热器通过电源与电源控制器（5）连接，温度传感器（3）与电源控制器连接以进行电子控制。 因此，防止了在极低温环境下通过CryoFit耦合器的膨胀破裂密封。
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公开(公告)号：KR100715786B1
公开(公告)日：2007-05-07
申请号：KR1020050129761
申请日：2005-12-26
Applicant: 한국항공우주연구원
Abstract: 본 발명의 인공위성용 태양센서 시험장치의 정렬방법은, 인공위성의 자세제어에 사용되는 태양센서의 성능 측정을 위한 장치들의 정렬에 있어 태양 센서에 비춰지는 모사된 태양광의 정확한 입사각을 측정하기 위한, 시험장치들의 정렬방법에 관한 것이다.
본 발명은, 태양광모사수단과 측정정렬장치로서의 오토콜리메이터(autocollimator) 간의 정렬을 제1단계로 수행한 후, 다시 태양센서를 거치시키는 회전테이블과 오토콜리메이터와 정렬시키는 제2단계로 진행하는 특징이 있다.
따라서 본 발명은, 태양광모사수단과 회전테이블 및 태양 센서의 회전 중심과 회전축을 정렬함으로써 태양 센서의 성능 시험 시 오정렬에 의한 오차를 줄여 측정 정확도를 향상시키는 효과를 제공한다.
태양 센서, 태양광 모사기, 정렬, 오토콜리메이터(autocollimator)Abstract translation: 本发明的用于卫星的太阳敏感器测试设备的对准方法的特征在于，为了测量用于卫星的姿态控制的太阳敏感器的性能， 对齐设备的方法。
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