-
公开(公告)号：WO2021194051A1
公开(公告)日：2021-09-30
申请号：PCT/KR2020/018340
申请日：2020-12-15
Applicant: 한국항공우주연구원
IPC: B64G1/28 , B64G1/10 , B64G1/283 , B64G2700/00
Abstract: 본 발명은 오프셋을 적용한 인공위성 반작용휠의 모멘텀 덤프 방법에 관한 것이다. 본 발명의 목적은, 원래 설계된 모멘텀 덤프에 대하여 적절한 오프셋을 적용함으로써 인공위성을 보다 안전하고 효율적으로 운용할 수 있도록 하는, 오프셋을 적용한 인공위성 반작용휠의 모멘텀 덤프 방법을 제공함에 있다.
-
公开(公告)号：WO2021125742A1
公开(公告)日：2021-06-24
申请号：PCT/KR2020/018339
申请日：2020-12-15
Applicant: 한국항공우주연구원
Abstract: 본 발명은 영속도가 방지되는 배치구조 및 회전방향을 가지는 반작용휠을 가지는 인공위성에 관한 것이다. 본 발명의 목적은 5개 이상의 반작용휠이 배치된 인공위성에 있어서, 모멘텀 바이어스의 사용 여부와 상관없이 영속도 방지가 가능하고, 또한 일부 휠이 고장나더라도 영속도를 방지하면서 정상적인 위성 자세제어 수행이 가능하게 하는, 영속도가 방지되는 배치구조 및 회전방향을 가지는 반작용휠을 가지는 인공위성을 제공함에 있다.
-
公开(公告)号：WO2015076510A1
公开(公告)日：2015-05-28
申请号：PCT/KR2014/010539
申请日：2014-11-05
Applicant: 한국항공우주연구원
Abstract: 본 발명은 인공위성에 관한 것으로서, 더욱 상세하게 태양 전지판이 비대칭으로 배치되는 인공위성에 있어서, 피라미드형으로 배치되는 4개의 휠을 포함하여 형성되되, 1개의 휠이 고장나더라도 영속도 전환 문제가 발생되지 않는 각도로 휠 배치 구조를 포함함으로써, 휠의 개수를 증가시키지 않고 단방향으로 운영할 수 있어 내란을 방지할 수 있으며, 가격 경쟁력을 확보할 수 있는 인공위성에 관한 것이다.
Abstract translation: 本发明涉及一种卫星，更具体地说，涉及一种具有非对称布置在其中的太阳能电池面板的卫星，该卫星包括四个以锥体形状布置的轮子，并具有轮子布置结构，其中轮子以一定角度排列，防止零 速度开关问题即使一个轮子发生故障也不会出现。 因此，可以在不增加车轮数量的情况下在单一方向上操作卫星，从而防止内部干扰并确保价格竞争力。
-
-
公开(公告)号：KR1020130076160A
公开(公告)日：2013-07-08
申请号：KR1020110144630
申请日：2011-12-28
Applicant: 한국항공우주연구원
Abstract: 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.
Abstract translation: 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。
-
Patent Agency Ranking
公开(公告)号：KR1020100078919A
公开(公告)日：2010-07-08
申请号：KR1020080137305
申请日：2008-12-30
Applicant: 한국항공우주연구원
CPC classification number: B64G1/24 , B64G1/443 , B64G2001/245 , G05D1/0883
Abstract: 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).
Abstract translation: 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）。
-
公开(公告)号：KR100780464B1
公开(公告)日：2007-11-28
申请号：KR1020060132845
申请日：2006-12-22
Applicant: 한국항공우주연구원
CPC classification number: G01C21/24 , B64G1/361 , G01C9/06 , G01C21/02 , G01C21/025
Abstract: 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.
Abstract translation: 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。
-
公开(公告)号：KR1020010058824A
公开(公告)日：2001-07-06
申请号：KR1019990066193
申请日：1999-12-30
IPC: B64G1/00
Abstract: 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.
Abstract translation: 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。
-
-
公开(公告)号：KR1020110066347A
公开(公告)日：2011-06-17
申请号：KR1020090122963
申请日：2009-12-11
Applicant: 한국항공우주연구원
Abstract: 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.
Abstract translation: 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）。
-
-
-
-
-
-
-
-
-
Search Results
29
records
(took 0.022 seconds)
