公开(公告)号：KR1020030018507A

公开(公告)日：2003-03-06

申请号：KR1020010052643

申请日：2001-08-30

Applicant: 한국항공우주연구원

Inventor： 박영웅 ,  최재동

IPC: G01C21/12

Abstract: PURPOSE: A propulsion system connecting apparatus is provided to allow a simulation of three-axis attitude control system of artificial satellites to be performed on the ground. CONSTITUTION: A propulsion system connecting apparatus comprises a penetrating clamp and a support clamp for fixing a compressed air tank(4) arranged in a downward direction at the outer surface of a frame(8); a penetrating clamp and a support clamp for fixing a compressed air tank(4') arranged in an upward direction at the outer surface of the frame; and pipelines of the compressed air tanks. The propulsion system connecting apparatus connects the penetrating clamps, support clamps, and the pipeline to a single unit and to thrust units(20,22,23,25) through constant pressure meters(28,29,30).

Abstract translation: 目的：提供推进系统连接装置，以便在地面上进行人造卫星三轴姿态控制系统的仿真。 构造：推进系统连接装置包括穿透夹具和用于固定在框架（8）的外表面处沿向下方向布置的压缩空气罐（4）的支撑夹具; 用于固定在框架的外表面沿向上方向布置的压缩空气罐（4'）的穿透夹具和支撑夹具; 和压缩空气罐的管道。 推进系统连接装置将穿透夹具，支撑夹具和管道连接到单个单元并且通过恒定压力计（28,29,30）推动单元（20,22,23,25）。

公开(公告)号：KR1020020048517A

公开(公告)日：2002-06-24

申请号：KR1020000077693

申请日：2000-12-18

Applicant: 한국항공우주연구원

Inventor： 박영웅

IPC: G01B11/14

Abstract: PURPOSE: A displacement sensing apparatus is provided to sense the rotating angle and displacement of inertia sensor in an accurate manner by using a simple device. CONSTITUTION: A central magnetic member(40) of an inertia sensor utilizing magnetic levitation system, has a rotating angle sensing reflector plate(20) and a displacement sensing reflector plate(30) which are attached to the central magnetic member. The inertia sensor has an external optical device for radiating light to the central magnetic member and sensing the light reflected from the rotating angle sensing reflector plate and the displacement sensing reflector plate. The reflector plates have surfaces which reflect light and other portions which do not reflect light. The surfaces reflecting light are formed into multiple columns, and have different widths in each column. The reflector plates have boundary reflecting surfaces formed at the outermost parts of the reflector plates, respectively.

Abstract translation: 目的：提供一种位移感测装置，通过使用简单的装置，以准确的方式感测惯性传感器的旋转角度和位移。 构成：利用磁悬浮系统的惯性传感器的中心磁性构件（40）具有附接到中心磁性构件的旋转角度检测反射板（20）和位移感测反射板（30）。 惯性传感器具有外部光学装置，用于将光照射到中心磁性部件并感测从旋转角度检测反射板和位移传感反射板反射的光。 反射板具有反射光和不反射光的其它部分的表面。 反射光的表面形成为多列，并且在每列中具有不同的宽度。 反射板分别在反射板的最外部形成边界反射面。

公开(公告)号：KR100250938B1

公开(公告)日：2000-04-15

申请号：KR1019970071143

申请日：1997-12-12

Applicant: 한국항공우주연구원 ,  주식회사 케이티

Inventor： 방효충 ,  박영웅 ,  한정엽

IPC: B64G7/00

Abstract: PURPOSE: An 1-axis rotation simulator is provided to allow a satellite to perform it's objects smoothly by sufficiently carrying out experiment on the ground before the satellite is departed. CONSTITUTION: An 1-axis rotation simulator comprises: a fixed horizontal strut(12); a rotary horizontal strut(20) rotatably combined to the upper portion of the fixed horizontal strut; a potentiometer(51) installed on the center of the rotary strut to detect position change of the rotary strut; a coupler(53) for fixing the potentiometer by coupling; an output unit installed on the rotary strut to generate rotational torque of the rotary strut; an angular speed sensor detecting angular speed of the rotary strut; and a data obtaining and operating unit for processing the obtained detecting data. The posture of the rotary horizontal strut is changed by a program stored in a posture control logic operating device. The 1-axis rotation simulator is applied to posture control of a satellite and general ground systems. As the 1-axis rotation simulator is produced at a low cost and replaced optionally, defrayment due to development is reduced.

Abstract translation: 目的：提供1轴旋转模拟器，以便在卫星离开之前，通过在地面上充分进行实验，可以使卫星顺利执行物体。 构成：1轴旋转模拟器包括：固定水平支柱（12）; 可旋转地组合到固定水平支柱的上部的旋转水平支柱（20） 安装在旋转支柱中心的电位计（51），以检测旋转支柱的位置变化; 用于通过耦合固定电位器的耦合器（53）; 安装在旋转支柱上以产生旋转支柱的旋转扭矩的输出单元; 检测所述旋转支柱的角速度的角速度传感器; 以及用于处理所获得的检测数据的数据获取和操作单元。 通过存储在姿势控制逻辑操作装置中的程序来改变旋转水平支柱的姿势。 1轴旋转模拟器适用于卫星和一般地面系统的姿势控制。 由于1轴旋转模拟器以低成本制造并且可替代地替换，所以由于显影而导致的减量。

公开(公告)号：KR102063212B1

公开(公告)日：2020-01-07

申请号：KR1020180033937

申请日：2018-03-23

Applicant: 한국항공우주연구원

Inventor： 박영웅

IPC: B64D45/06 ,  B64C39/02

公开(公告)号：KR101059436B1

公开(公告)日：2011-08-25

申请号：KR1020080137294

申请日：2008-12-30

Applicant: 한국항공우주연구원

Inventor： 이훈희 ,  박영웅

IPC: B64G1/44 ,  B64G1/42

Abstract: 본 발명은 인공위성의 양 측면에 구동부에 의해 출몰 가능하도록 설치되는 지지축과, 상기 지지축의 외단부에 설치되며 적어도 하나 이상의 설치면을 갖는 지지부재와, 상기 지지부재의 각 설치면에 설치되되, 태양전지판에 연결되어 태양전지판을 회전시키는 다수의 회전모터로 구성되는 것을 특징으로 한다.
본 발명에 의하면, 태양전지판을 구동시키는 구동장치의 구조를 변경함으로써 인공위성의 양 측면 각각에 다수의 태양전지판을 설치할 수 있고, 다수의 태양전지판이 각각 회전할 수 있게 되어, 태양전지판을 과도하게 연장하지 않으면서 필요전력을 발생시킬 수 있으며, 인공위성의 모멘텀 덤핑도 수행할 수 있는 효과가 있다.
인공위성, 태양전지판, 구동장치, 지지부재, 지지축

Abstract translation: 本发明是安装在支承轴和支承轴，它安装在驱动单元上安装的支撑构件的每个安装表面上的卫星doedoe的任一侧是侵扰的外端，具有安装表面的至少一个支撑构件， 连接到太阳能电池板以旋转太阳能电池板的多个旋转电机。

公开(公告)号：KR1020080058748A

公开(公告)日：2008-06-26

申请号：KR1020060132821

申请日：2006-12-22

Applicant: 한국항공우주연구원

Inventor： 박근주 ,  주광혁 ,  박영웅 ,  이훈희

IPC: G01C7/04 ,  G01C21/02 ,  H04N5/21

CPC classification number: G01C7/04 ,  G01C15/00 ,  G01C21/02 ,  G01C25/00 ,  H04N5/21

Abstract: An image correction system for a star sensor and a star sensor system capable of canceling jitter are provided to improve attitude determination of a spacecraft by compensating a distorted image to use the compensated image for attitude control of the spacecraft. An image correction system(20) for a star sensor comprises an optical system(2), a CCD imager(3), a plurality of accelerometers(21), a band-pass signal processing unit(22), and an image compensating and processing unit(23). The optical system condenses light of a star and enlarges/reduces an image of the star. The CCD imager is coaxially mounted with the optical system, and senses the star image that is enlarged or reduced by the optical system. The accelerometers are mounted on the CCD imager to measure acceleration of the jitter of the CCD imager in a direction of at least one azimuthal axis. The signal processor performs double integration on the acceleration information measured by the accelerometers to calculate displacement of the CCD imager in a direction of each azimuthal axis, and calculates amplitude of the displacement in a direction of each azimuthal axis by deducting the minimum from the maximum of the displacement. The image compensating and processing unit corrects the image of the star by extracting coordinates of the star image on an image plane of the CCD imager, deducting the amplitude from the extracted coordinates, and arranging the star image on the deducted coordinates so as to correct the star image.

Abstract translation: 提供了一种能够消除抖动的星形传感器和星形传感器系统的图像校正系统，以通过补偿失真的图像来改进航天器的姿态确定，以使用补偿的图像来进行航天器的姿态控制。 用于星形传感器的图像校正系统（20）包括光学系统（2），CCD成像器（3），多个加速度计（21），带通信号处理单元（22），以及图像补偿和 处理单元（23）。 光学系统凝结星星的光，并放大/缩小星的图像。 CCD成像仪与光学系统同轴安装，并感测由光学系统放大或缩小的星形图像。 加速度计安装在CCD成像器上，以测量CCD成像器在至少一个方位轴的方向上的抖动的加速度。 信号处理器对由加速度计测量的加速度信息执行双重积分，以计算CCD成像器在每个方位轴的方向上的位移，并且通过从每个方位角的方向减去最大值 位移。 图像补偿处理单元通过提取CCD成像器的图像平面上的星形图像的坐标来校正星的图像，从提取的坐标中减去振幅，并将星形图像排列在扣除的坐标上，以校正 明星形象。

公开(公告)号：KR1020040026961A

公开(公告)日：2004-04-01

申请号：KR1020020058621

申请日：2002-09-27

Applicant: 한국항공우주연구원

Inventor： 박영웅

IPC: B64G1/10

Abstract: PURPOSE: Pyramid-type reaction wheel momentum management algorithm of a geostationary orbit artificial satellite is provided to automatically manage the reaction wheel algorithm by separately discriminating the momentum management algorithm at a dumping mode and a station keeping mode. CONSTITUTION: Pyramid-type reaction wheel momentum(W1,W2,W3,W4) management algorithm of a geostationary orbit artificial satellite automatically manages steps of deciding dumping execution by separating a stable region and a normal operation range for the current reaction wheel momentum, separately considering a thruster set for four reaction wheels, and then deciding a thruster set adequate to produce torque in 3-axis directions. At a station keeping mode, the pyramid-type reaction wheel momentum management algorithm of the geostationary orbit artificial satellite calculates a torque value to be controlled for disturbance, decides the dumping state when the reaction wheel momentum is not in the stable region, and executes attitude control, using reaction wheels when the torque direction to be controlled and the torque direction to be dumped are not coincided.

Abstract translation: 目的：提供地球静止轨道人造卫星的金字塔式反应轮动量管理算法，通过在倾卸模式和站保持模式下分别区分动量管理算法，自动管理反作用轮算法。 构成：地球静止轨道人造卫星的金字塔式反应轮动量（W1，W2，W3，W4）管理算法通过分离当前反作用轮动量的稳定区域和正常工作范围来自动管理决定倾倒执行的步骤 考虑用于四个反作用轮的推进器，然后确定一个足以在3轴方向产生扭矩的推进器组。 在站保持模式下，地球静止轨道人造卫星的金字塔式反应轮动量管理算法计算出受干扰控制的转矩值，当反作用轮动量不在稳定区域时决定倾倒状态，并执行姿态 当要控制的扭矩方向和要转储的转矩方向不一致时，使用反作用轮。

公开(公告)号：KR100384491B1

公开(公告)日：2003-05-22

申请号：KR1020000077693

申请日：2000-12-18

Applicant: 한국항공우주연구원

Inventor： 박영웅

IPC: G01B11/14

Abstract: PURPOSE: A displacement sensing apparatus is provided to sense the rotating angle and displacement of inertia sensor in an accurate manner by using a simple device. CONSTITUTION: A central magnetic member(40) of an inertia sensor utilizing magnetic levitation system, has a rotating angle sensing reflector plate(20) and a displacement sensing reflector plate(30) which are attached to the central magnetic member. The inertia sensor has an external optical device for radiating light to the central magnetic member and sensing the light reflected from the rotating angle sensing reflector plate and the displacement sensing reflector plate. The reflector plates have surfaces which reflect light and other portions which do not reflect light. The surfaces reflecting light are formed into multiple columns, and have different widths in each column. The reflector plates have boundary reflecting surfaces formed at the outermost parts of the reflector plates, respectively.

Abstract translation: 目的：提供一种位移传感装置，通过使用简单的装置来精确地感测惯性传感器的旋转角度和位移。 本发明涉及一种利用磁悬浮系统的惯性传感器的中央磁性部件（40），其具有安装在中央磁性部件上的旋转角度检测反射板（20）和位移检测反射板（30）。 惯性传感器具有外部光学装置，用于将光辐射到中央磁性构件并且感测从旋转角度感测反射板和位移感测反射板反射的光。 反射板具有反射光的表面和其他不反射光的部分。 反射光的表面被形成为多列，并且在每列中具有不同的宽度。 反射板分别具有形成在反射板最外部的边界反射表面。

公开(公告)号：KR100369434B1

公开(公告)日：2003-01-24

申请号：KR1019990066190

申请日：1999-12-30

Applicant: 주식회사 케이티 ,  한국항공우주연구원

Inventor： 박영웅 ,  방효충 ,  한정엽

IPC: B64G1/00

Abstract: PURPOSE: A triaxial position controlling structure for a satellite is provided to reduce load by removing unnecessary area of the structure and to easily insert the structure by attaching a guide structure. CONSTITUTION: A triaxial position controlling structure comprises a satellite simulation structure(1) installing components on a vertical plate(2) and a horizontal plate(3); a screw groove(4) installed on the horizontal plate with a specific interval to conveniently arrange the component; a space(6) formed on the horizontal plate and the vertical plate to reduce load; a guide structure(5) vertically attached on the vertical plate to easily insert the horizontal plate; and a middle horizontal plate(3) fixed on an air bearing(7) to lower specific gravity of the satellite simulation structure. The load of the air bearing is reduced by removing the unnecessary space of the horizontal and vertical plates of the satellite simulation structure. Moreover, the space and the screw groove arrange assembled components without releasing the satellite simulation structure.

Abstract translation: 目的：提供用于卫星的三轴位置控制结构，以通过去除结构的不必要区域来减轻负载，并通过附接引导结构来容易地插入结构。 一种三轴位置控制结构，包括卫星模拟结构（1），在垂直板（2）和水平板（3）上安装部件; 螺丝槽（4）以特定的间隔安装在水平板上以方便地布置元件; 在水平板和垂直板上形成的空间（6）以减少负载; 垂直安装在垂直板上以便容易插入水平板的导向结构（5） 和固定在空气轴承（7）上的中间水平板（3），以降低卫星模拟结构的比重。 通过去除卫星模拟结构的水平和垂直板的不必要空间，减少了空气轴承的负荷。 而且，空间和螺纹槽在不释放卫星模拟结构的情况下布置组装的部件。