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公开(公告)号：KR100366947B1
公开(公告)日：2003-01-09
申请号：KR1020000046145
申请日：2000-08-09
Applicant: 한국항공우주연구원
IPC: G09B9/52
Abstract: PURPOSE: Provided is a position control experiment equipment for an artificial satellite which adjusts the height of copy structure for the artificial satellite to move weight center of the structure up and down so that it helps to coincide weight center of copy structure with rotation center of air bearing in an easy way. CONSTITUTION: The position control experiment equipment for the artificial satellite is characterized by fixing an up/down bolt with a screw formed outside at the intermediate lower part of the copy structure for the artificial satellite, interpolating the up/down bolt between a guide road in the upper part of the air bearing and a screw housing and inserting a nut into the exterior side of the up/down bolt to ride on a key and move up and down as the nut is rotated.
Abstract translation: 目的：提供一种用于人造卫星的位置控制实验设备，其调整人造卫星的复制结构的高度以上下移动结构的重心以便使复制结构的重心与空气的旋转中心一致 以简单的方式承载。 组成：人造卫星的位置控制实验装置的特征在于，在人造卫星的复制结构的中间下部外侧固定一个带有螺钉的上/下螺栓，将上/下螺栓插入到引导道 空气轴承的上部和螺钉壳体，并且将螺母插入上/下螺栓的外侧以骑在钥匙上并随着螺母旋转而上下移动。
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公开(公告)号：KR1020130042337A
公开(公告)日：2013-04-26
申请号：KR1020110106585
申请日：2011-10-18
Applicant: 한국항공우주연구원
CPC classification number: G01C19/065 , G01C19/18 , G01L3/00 , G01P15/14
Abstract: PURPOSE: A one-way high power torque driving device and a one-way high power torque driving method are provided to generate torque of high power in one way. CONSTITUTION: A one-way high power torque driving device comprises a control moment gyroscope(410), a first reaction wheel(420), and a second reaction wheel(430). The control moment gyroscope is connected to a gimbal, and the reaction wheel rotates around a gimbal shaft. The first reaction wheel is installed on a vertical plane with the gimbal shaft. The second reaction wheel is installed at a same plane to the first reaction wheel and comprises a right angle with the first reaction wheel.
Abstract translation: 目的：提供单向高功率转矩驱动装置和单向高功率转矩驱动方法，以一种方式产生高功率的转矩。 构成：单向高功率扭矩驱动装置包括控制力矩陀螺仪（410），第一反作用轮（420）和第二反作用轮（430）。 控制时刻陀螺仪连接到万向节，反作用轮绕万向轴旋转。 第一个反作用轮安装在带万向轴的垂直平面上。 第二反作用轮安装在与第一反作用轮相同的平面上，并且与第一反作用轮成直角。
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公开(公告)号：KR1020120032248A
公开(公告)日：2012-04-05
申请号：KR1020100093798
申请日：2010-09-28
Applicant: 한국항공우주연구원
Inventor： 이승우
IPC: G01C19/02
CPC classification number: G01C19/065 , G01C19/08 , G01P9/02 , G01P15/14
Abstract: PURPOSE: A control moment gyroscope and a controlling method of the maximum allowable output torque thereof are provided to control the maximum rotary velocity of a gimbal shaft at an arbitrary velocity so that the maximum allowable output torque is arbitrarily set and an utilization range of a control moment gyroscope is extended. CONSTITUTION: A control moment gyroscope comprises a momentum wheel, a gimbal frame(120), a gimbal motor(140), and a transmission(150). The momentum wheel supplies an angular momentum vector by rotary-driving of a rotational plate(112). The gimbal frame supports the momentum wheel so that the momentum wheel rotates around a shaft which is vertical with respect to a rotary shaft of the rotational plate. The gimbal motor is installed in the outer side of the gimbal frame and rotary-drives the momentum wheel. The transmission changes a rotary velocity of the gimbal motor into a plurality of transmission rates to control the maximum gimbal rotary velocity of the momentum wheel.
Abstract translation: 目的：提供一种控制力矩陀螺仪及其最大允许输出转矩的控制方法，以任意速度控制万向轴的最大转速，使得最大允许输出转矩被任意设定，控制方式的使用范围 时间陀螺仪被扩展。 构成：控制力矩陀螺仪包括动量轮，万向架（120），万向电动机（140）和变速器（150）。 动量轮通过旋转盘（112）的旋转驱动来提供角动量矢量。 万向架框架支撑动量轮，使得动量轮围绕相对于旋转板的旋转轴垂直的轴旋转。 万向架电机安装在万向架框架的外侧，并旋转驱动动量轮。 传动装置将万向电机的旋转速度改变为多个传输速率，以控制动量轮的最大万向旋转速度。
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公开(公告)号：KR1020060076548A
公开(公告)日：2006-07-04
申请号：KR1020040115007
申请日：2004-12-29
Applicant: 한국항공우주연구원
Abstract: 본 발명은 인공위성에 장착된 3축 자기센서를 통해서 위성좌표계에서 지구자기장을 측정하는 단계(S1); 지구지향모드에서 측정된 지구 자기장데이터를 지구지향변환좌표계로 변환하고 태양지향모드에서 측정된 지구 자기장데이터를 태양지향변환좌표계로 변환하여 변환자기장을 산출하는 변환자기장 산출단계(S2); 변환자기장의 시평균값을 계산하는 시평균값 산출단계(S3); 시평균값을 지구지향변환좌표계에서 지구지향모드 위성좌표계로, 태양지향변환좌표계에서 태양지향모드 위성체좌표계로 역변환후 곡선접합법을 적용하여 측정된 자기장 데이터에 포함된 바이어스를 산출하는 바이어스 산출단계(S4); 산출된 바이어스를 측정된 자기장 데이터에서 소거하여 보정을 완료하는 바이어스 보정단계(S5);로 이루어지는 것을 특징으로 하는 궤도기하학을 이용한 인공위성 자기센서의 바이어스 보정방법에 관한 것이다.
인공위성 자기센서, 바이어스 보정, 궤도기하학-
Patent Agency Ranking
公开(公告)号：KR1020160074242A
公开(公告)日：2016-06-28
申请号：KR1020140183320
申请日：2014-12-18
Applicant: 한국항공우주연구원
CPC classification number: B64G1/28 , B64C17/06 , B64G1/10 , Y10S384/906
Abstract: 비행체의자세제어를위해탑재되는제어모멘트자이로(Control Moment Gyroscope) 클러스터를제어하는장치가제공된다. 상기제어모멘트자이로클러스터의제어장치는, 제어모멘트자이로클러스터를구성하는적어도하나의제어모멘트자이로의휠 회전에따른각 운동량및 김벌모터의각속도를이용하여, 비행체의자세제어를위한토크신호를발생시키는토크발생부, 및상기김벌모터의각속도에영운동제어신호및 디더제어신호를포함하는제어루프를적용하는제어부부를포함할수 있다.
Abstract translation: 提供了一种用于控制安装以控制飞行器的姿势的控制力矩陀螺仪的集群的装置。 用于控制控制力矩陀螺仪的集群的装置包括：转矩产生单元，其根据至少控制的车轮旋转产生用于使用万向电机的角速度和角动量来控制飞行器车辆的姿势的转矩信号 矩形陀螺仪形成控制力矩陀螺仪的集群; 以及控制单元，其将包括抖动控制信号和零运动控制信号的控制回路施加到万向马达的角速度。
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公开(公告)号：KR1020120075812A
公开(公告)日：2012-07-09
申请号：KR1020100137668
申请日：2010-12-29
Applicant: 한국항공우주연구원
CPC classification number: B64G7/00
Abstract: PURPOSE: An inspection device for a three-axis posture control is provided to preciously perform a three-axis posture control inspection by providing an inspection circumstance similar to a cosmic environment and to preciously analyze performance of a satellite in the actual cosmic environment. CONSTITUTION: An inspection device for a three-axis posture control comprises a support unit(110), a ball bearing unit(120) for supporting, a ball bearing unit(130) for rotation, and a mounting unit(140). The support unit is formed at a constant height. The ball bearing unit for supporting is fixed on the top of the supporting unit and formed into a cylindrical shape in which an opening is formed on the top and a ball bearing unit is formed along the inner circumference of the opening. The bottom of the ball bearing unit is inserted into the opening, thereby being seated in the ball bearing unit. The ball bearing unit for rotation is supported to be rotated by the ball bearing unit. An inspection object for a three-axis posture control test is placed on the mounting unit.
Abstract translation: 目的：提供一种用于三轴姿势控制的检查装置，通过提供与宇宙环境相似的检查环境，并珍贵地分析实际宇宙环境中的卫星的性能，进行三轴姿态控制检查。 构成：用于三轴姿势控制的检查装置包括支撑单元（110），用于支撑用于旋转的滚珠轴承单元（130）的滚珠轴承单元（120）和安装单元（140）。 支撑单元形成为恒定的高度。 用于支撑的滚珠轴承单元固定在支撑单元的顶部上并形成为在顶部形成有开口的圆柱形状，并且沿着开口的内圆周形成滚珠轴承单元。 滚珠轴承单元的底部插入开口中，从而位于滚珠轴承单元中。 用于旋转的滚珠轴承单元由球轴承单元支撑以旋转。 用于三轴姿势控制测试的检查对象放置在安装单元上。
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公开(公告)号：KR1020100066950A
公开(公告)日：2010-06-18
申请号：KR1020080125478
申请日：2008-12-10
Applicant: 한국항공우주연구원
CPC classification number: G01C19/30 , Y10T74/12 , Y10T74/1229
Abstract: PURPOSE: A control moment gyroscope is provided to obtain a vibration attenuation effect by miniaturizing the product of inertia by maintaining the balance of mass to gimbal rotating shaft. CONSTITUTION: A control moment gyroscope comprises a gimbal rim, a wheel frame(200), a first momentum wheel(310), a second momentum wheel(320), a gimbal motor(400), and a measurement sensor. The wheel frame comprises a first frame(210) and a second frame(220). The first frame is located in the gimbal rim. The second frame is coupled to have the same structure as the first frame and to be symmetrical to the first frame. The first momentum wheel is coupled to the first frame. The second momentum wheel is coupled to the location corresponding to the first momentum wheel of the second frame. The gimbal motor is installed on one side of the surface of the gimbal rim. The measurement sensor is installed on the other side of the surface of the gimbal rim. The measurement sensor is connected to the other ends of the first and second frames to measure the angular velocity of the first and second frames.
Abstract translation: 目的：提供控制力矩陀螺仪，通过将质量平衡保持在万向转轴上，通过使惯性乘积小型化来获得振动衰减效果。 构成：控制力矩陀螺仪包括万向架，轮架（200），第一动量轮（310），第二动量轮（320），万向电动机（400）和测量传感器。 轮架包括第一框架（210）和第二框架（220）。 第一个框架位于万向架边框中。 第二框架被联接成具有与第一框架相同的结构并且与第一框架对称。 第一动量轮连接到第一框架。 第二动量轮联接到对应于第二框架的第一动量轮的位置。 万向电机安装在万向架轮辋表面的一侧。 测量传感器安装在万向架边缘表面的另一侧。 测量传感器连接到第一和第二框架的另一端以测量第一和第二框架的角速度。
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公开(公告)号：KR1020020050329A
公开(公告)日：2002-06-27
申请号：KR1020000079452
申请日：2000-12-21
Applicant: 한국항공우주연구원
IPC: G01M99/00
CPC classification number: B64G7/00 , B64G1/44 , G01N17/002
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，使用户能够在地球上观察安装在宇宙中的人造卫星的太阳能电池板的爆炸，通过设备以简化的结构和降低的成本，同时提高测试的可靠性。 构成：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; 引导梁（12）布置成用于在地球上实现无重力状态并且爆炸太阳能电池板的蹦极缆绳; 一个用于通过向氮液罐（17），蒸发器（18）和氮气供应泵（19）供应低温氮气（20）来提供低温环境的绝热箱; 以及连接到加热器以便操作额外的小摩擦轴承的功率控制器（22）和电源（21）。
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公开(公告)号：KR1020020049433A
公开(公告)日：2002-06-26
申请号：KR1020000078602
申请日：2000-12-19
Applicant: 한국항공우주연구원
IPC: G05D23/30
Abstract: PURPOSE: A thermal control device using a PID(Proportional Integral Differential) feedback current control method is provided to control accurately temperature by improving accuracy in a process for controlling power of a heater. CONSTITUTION: A control computer(1) includes a software executing a PID control loop. The control computer(1) is used for processing and storing all data. A GPIB card is mounted in the control computer(1). A master rack(2) is formed with a command control unit(3), a data acquisition module(4), and an interface unit(5). The command control unit(3) distributes commands of the control computer(1) to sub-modules. The data acquisition module(4) measures temperature, voltage, and current. The interface unit(5) assigns a command value to a power supply(10). A fuse/switch module(6) is formed with a fuse(7) and a toggle switch(8). A power supply rack(9) includes a multitude of power supply. The number of power supply corresponds to the number of heater(13). A shunt box module(11) includes a shunt register. The heater(13) and a thermocouple(14) are adhered to a thermal control portion(12).
Abstract translation: 目的：提供使用PID（比例积分微分）反馈电流控制方法的热控制装置，通过提高加热器功率的控制过程中的精度来精确控制温度。 构成：控制计算机（1）包括执行PID控制回路的软件。 控制计算机（1）用于处理和存储所有数据。 GPIB卡安装在控制计算机（1）中。 主机架（2）形成有指令控制单元（3），数据采集模块（4）和接口单元（5）。 命令控制单元（3）将控制计算机（1）的命令分配给子模块。 数据采集模块（4）测量温度，电压和电流。 接口单元（5）向电源（10）分配命令值。 保险丝/开关模块（6）形成有保险丝（7）和拨动开关（8）。 电源机架（9）包括多个电源。 电源数量相当于加热器的数量（13）。 分路盒模块（11）包括分路寄存器。 加热器（13）和热电偶（14）粘附到热控制部分（12）。
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