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1. 发明授权

KR102040976B1 차량 안전 파킹 장치 및 방법 有权
公开(公告)号：KR102040976B1
公开(公告)日：2019-11-05
申请号：KR1020180033169
申请日：2018-03-22
申请人： 한국항공우주연구원
发明人： 박영웅
IPC分类号： B60W10/18 , B60W50/08 , B60R25/10 , B60R21/015 , B60N2/00 , B60W40/08

2. 发明公开

KR1020130076160A 컨트롤 모멘텀 자이로스코프 장착 차량 无效
标题翻译：具有控制动力学陀飞轮的车辆系统
公开(公告)号：KR1020130076160A
公开(公告)日：2013-07-08
申请号：KR1020110144630
申请日：2011-12-28
申请人： 한국항공우주연구원
发明人： 박영웅 , 김대관
IPC分类号： B61D49/00 , G01C19/02 , G05D1/08
摘要： PURPOSE: A control momentum gyroscope (CMG) installed vehicle is provided to compensate rotatory power which is generated when the speed of the vehicle is additionally increased by using the torque of a CMG, thereby preventing derailment or overturn of a vehicle which is caused by the rotatory power. CONSTITUTION: A control momentum gyroscope (CMG) (200) installed vehicle comprises at least one CMG. Each vehicle is equipped with one CMD in case of a train (100) to which multiple vehicles are connected. The progressive direction (V) of the vehicle and the axis of torque of the CMD are configured horizontally when the CMD is installed.
摘要翻译：目的：提供一种控制动力陀螺仪（CMG）安装车辆，用于补偿通过使用CMG的扭矩来额外增加车辆速度时产生的旋转动力，从而防止因车辆引起的脱轨或翻倒旋转力。构成：控制动力陀螺仪（CMG）（200）安装车辆包括至少一个CMG。在车辆连接多个车辆的情况下，每辆车辆配备有一个CMD。当安装CMD时，车辆的行进方向（V）和CMD的扭矩轴水平配置。

3. 发明公开

KR1020100078919A 태양전지판을 이용한 인공위성 자세제어장치 및 그 방법 有权
标题翻译：卫星运动控制装置及其使用太阳辐射阵列的方法
公开(公告)号：KR1020100078919A
公开(公告)日：2010-07-08
申请号：KR1020080137305
申请日：2008-12-30
申请人： 한국항공우주연구원
发明人： 박영웅 , 이훈희
IPC分类号： B64G1/44 , B64G1/24 , G05D1/08
CPC分类号： B64G1/24 , B64G1/443 , B64G2001/245 , G05D1/0883
摘要： PURPOSE: Pose control device and method of a satellite using a solar panel are provided to save the fuel of a satellite by eliminating the need to use a thruster for momentum dumping even capable of being performed under a small reaction torque. CONSTITUTION: A pose control device of a satellite using a solar panel comprises a support shaft(200), a support member(300), and a step motor. The support shaft is installed on both sides of a satellite to be able to be disappeared by a driving unit. The support member is installed on the outer end of the support shaft. The support member includes one or more installation surfaces. The step motor is installed on the installation surface of the support member. The step motor is connected to a solar panel. The step motor rotates the solar panel. The step motor includes a first step motor(400) and a second step motor(410).
摘要翻译：目的：提供使用太阳能电池板的卫星的姿态控制装置和方法，以便通过消除对即使能够在小的反作用力矩下执行的用于动量倾倒的推进器的需要来节省卫星的燃料。构成：使用太阳能电池板的卫星的姿态控制装置包括支撑轴（200），支撑构件（300）和步进电动机。支撑轴安装在卫星的两侧，以便能够被驱动单元消失。支撑构件安装在支撑轴的外端上。支撑构件包括一个或多个安装表面。步进马达安装在支撑件的安装表面上。步进电机连接到太阳能电池板。步进电机旋转太阳能电池板。步进电动机包括第一步进电动机（400）和第二步进电动机（410）。

4. 发明授权

KR100780464B1 별센서에서의 별 중심찾기 방법 失效
标题翻译：基于STAR传感器的自适应星形中心方法
公开(公告)号：KR100780464B1
公开(公告)日：2007-11-28
申请号：KR1020060132845
申请日：2006-12-22
申请人： 한국항공우주연구원
发明人： 주광혁 , 박영웅 , 박근주 , 이훈희
IPC分类号： G01C21/24 , G01C21/02
CPC分类号： G01C21/24 , B64G1/361 , G01C9/06 , G01C21/02 , G01C21/025
摘要： A method for finding centroid of an adaptive star in a star sensor is provided to improve accuracy and speed in star pattern recognition and pose decision by previously removing unusual stars in a cluster forming process. A method for finding centroid of an adaptive star in a star sensor includes the steps of: compensating dark current in a star image photographed by a CCD(Charge-Coupled Device) in a star sensor; measuring average brightness of a background image corresponding to an outer space from a selected scan window to separate the star image displayed on the CCD from the background image corresponding to the outer space; selecting the minimum effective brightness level from the average brightness of the background image of the outer space; detecting valid pixels above the minimum effective brightness level; forming a cluster with valid pixels above the minimum effective brightness level; removing stars with unusual shape in the cluster; and calculating centroid of the clustered star with a centroid method.
摘要翻译：提供了一种用于在星形传感器中发现自适应星的质心的方法，以提高星型图识别中的精度和速度，并通过先前在簇形成过程中去除不寻常恒星来构成决策。一种用于在恒星传感器中发现自适应星的质心的方法包括以下步骤：补偿由星形传感器中的CCD（电荷耦合器件）拍摄的星形图像中的暗电流; 测量从所选择的扫描窗口对应于外部空间的背景图像的平均亮度，以将显示在CCD上的星形图像与对应于外部空间的背景图像分离; 从外部空间的背景图像的平均亮度中选择最小有效亮度水平; 检测高于最小有效亮度水平的有效像素; 形成具有高于最低有效亮度水平的有效像素的聚类; 在群集中除去异常形状的星星; 并用质心法计算聚类星的质心。

5. 发明公开

KR1020010058824A 인공위성의 3축 자세제어 실험장치 失效
标题翻译：用于测试卫星三角位置控制的装置
公开(公告)号：KR1020010058824A
公开(公告)日：2001-07-06
申请号：KR1019990066193
申请日：1999-12-30
申请人： 주식회사 케이티 , 한국항공우주연구원
发明人： 박영웅 , 방효충 , 한정엽
IPC分类号： B64G1/00
摘要： PURPOSE: A triaxial position control testing device of a satellite is provided to inspect a triaxial position control system on a ground. CONSTITUTION: A triaxial position control testing device comprises a satellite simulation structure(1) of a hexahedron mounting structure; an air bearing(2) flying the satellite simulation structure by compression air(7); nozzles(4,5,6) generating position control thrust of the satellite simulation structure by being applied the compression air; and a mounted computer controlling driving of the nozzle according to a position control sensor input. The air bearing is fixed on a middle plate(3) to lower specific gravity by installing the mounted component of the satellite in the satellite simulation structure. Thrust of the satellite simulation structure injects thrust by the compression air.
摘要翻译：目的：提供卫星的三轴位置控制测试装置，以检查地面上的三轴位置控制系统。构成：三轴位置控制测试装置包括六面体安装结构的卫星仿真结构（1）; 空气轴承（2）通过压缩空气（7）飞行卫星模拟结构; 喷嘴（4,5,6）通过施加压缩空气产生卫星模拟结构的位置控制推力; 以及安装的计算机，其根据位置控制传感器输入来控制喷嘴的驱动。通过将卫星的安装部件安装在卫星模拟结构中，将空气轴承固定在中间板（3）上以降低比重。卫星模拟结构的推力通过压缩空气喷射推力。

6. 发明授权

KR102250118B1 오프셋을 적용한 인공위성 반작용휠의 모멘텀 덤프 방법 有权
公开(公告)号：KR102250118B1
公开(公告)日：2021-05-10
申请号：KR1020200036120
申请日：2020-03-25
申请人： 한국항공우주연구원
发明人： 윤형주 , 박영웅
IPC分类号： B64G1/28 , B64G1/10
摘要： 본발명은오프셋을적용한인공위성반작용휠의모멘텀덤프방법에관한것이다. 본발명의목적은, 원래설계된모멘텀덤프에대하여적절한오프셋을적용함으로써인공위성을보다안전하고효율적으로운용할수 있도록하는, 오프셋을적용한인공위성반작용휠의모멘텀덤프방법을제공함에있다.

7. 发明公开

KR1020110066347A 진동 및 충격 차단 장치 无效
标题翻译：振动和冲击隔离装置
公开(公告)号：KR1020110066347A
公开(公告)日：2011-06-17
申请号：KR1020090122963
申请日：2009-12-11
申请人： 한국항공우주연구원
发明人： 김대관 , 박영웅 , 오시환 , 양군호 , 용기력
IPC分类号： F16F15/08 , F16F15/02
摘要： PURPOSE: A vibration and shock isolation device is provided to cut off vibration according to frequency through passive, semi-active, and active control of elastic members. CONSTITUTION: A vibration and shock isolation device(100) comprises one or more elastic members(130) which are interposed between a vibrating facility(200) and a structure(300). The elastic members include active elastomer(131) whose elastic coefficient and damping coefficient change according to voltage and passive elastomer(133) having fixed elastic coefficient and damping coefficient.
摘要翻译：目的：提供振动和冲击隔离装置，通过弹性构件的被动，半主动和主动控制，根据频率切断振动。构成：振动和冲击隔离装置（100）包括介于振动设备（200）和结构（300）之间的一个或多个弹性构件（130）。弹性构件包括其弹性系数和阻尼系数根据电压而变化的活性弹性体（131）和具有固定的弹性系数和阻尼系数的无源弹性体（133）。

8. 发明公开

KR1020100078911A 인공위성용 다중 태양전지판의 구동장치 失效
标题翻译：用于卫星的多个太阳能阵列的驱动装置
公开(公告)号：KR1020100078911A
公开(公告)日：2010-07-08
申请号：KR1020080137294
申请日：2008-12-30
申请人： 한국항공우주연구원
发明人： 이훈희 , 박영웅
IPC分类号： B64G1/44 , B64G1/42
CPC分类号： B64G1/24 , B64G1/443
摘要： PURPOSE: A drive unit of the multiple solar arrays for a satellite is provided to install a plurality of solar arrays on both sides of a satellite by changing the structure of a driving unit with a high-temperature fluid blocking valve. CONSTITUTION: A high-temperature fluid blocking valve comprises a support shaft(200), a support member(300), and a rotating motor(500). The support shaft is installed on both sides of the satellite to be able to be disappeared by a driving unit. The support member is installed on the outer end of the support shaft. The support member includes one or more installation surfaces. The rotating motor is installed on the installation surfaces of the support member. The rotating motor is connected to a solar array. The rotating motor rotates the solar array.
摘要翻译：目的：提供用于卫星的多个太阳能阵列的驱动单元，以通过用高温流体阻断阀改变驱动单元的结构来在卫星的两侧上安装多个太阳能阵列。构成：高温流体阻塞阀包括支撑轴（200），支撑构件（300）和旋转马达（500）。支撑轴安装在卫星的两侧，以便能够被驱动单元消失。支撑构件安装在支撑轴的外端上。支撑构件包括一个或多个安装表面。旋转马达安装在支撑件的安装表面上。旋转马达连接到太阳能阵列。旋转电机旋转太阳能电池阵列。

9. 发明公开

KR1020010058821A 인공위성의 3축 자세제어 구조물 失效
标题翻译：卫星三重位置控制结构
公开(公告)号：KR1020010058821A
公开(公告)日：2001-07-06
申请号：KR1019990066190
申请日：1999-12-30
申请人： 주식회사 케이티 , 한국항공우주연구원
发明人： 박영웅 , 방효충 , 한정엽
IPC分类号： B64G1/00
摘要： 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.
摘要翻译：目的：提供一种用于卫星的三轴位置控制结构，通过去除结构的不必要区域，并通过安装引导结构容易地插入结构来减轻负载。构成：三轴位置控制结构包括在垂直板（2）和水平板（3）上安装部件的卫星模拟结构（1）。以特定间隔安装在水平板上的螺丝槽（4），以方便地布置部件; 形成在水平板和垂直板上的空间（6），以减轻负载; 垂直安装在垂直板上的引导结构（5），以便容易地插入水平板; 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的空间来减小空气轴承的负载。此外，空间和螺纹槽布置组装的部件，而不会释放卫星模拟结构。

10. 发明授权

KR100942010B1 위성용 우주분진물 분사장치 失效
标题翻译：使用弹性能量在卫星上发射碎片的装置
公开(公告)号：KR100942010B1
公开(公告)日：2010-02-12
申请号：KR1020070140751
申请日：2007-12-28
申请人： 한국항공우주연구원
发明人： 박영웅 , 주광혁 , 박근주 , 이훈희
IPC分类号： B64G1/22
摘要： 본 발명은 위성용 우주분진물 분사장치에 관한 것으로서, 우주분진물을 수거하는 위성에 탑재된 분사장치에 있어서, 상기 분사장치는, 개구된 일단부로 우주분진물이 분사되는 본체와; 상기 본체에 삽입되어 내장되고 그 일단부는 수거된 우주분진물과 접하는 분사면으로 형성된 스프링과; 상기 본체에 설치되고 모터에 의해 회전 구동되는 스크류축과; 상기 스크류축에 의해 본체의 축방향을 따라 이동되면서 스프링을 압축 및 인장시키는 고정핀;을 포함하여 구성된 것을 특징으로 하여, 경제적이고 효율적이다.
위성, 우주, 분진물, 잔해, 분사, 대기권, 스프링, 분사면

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