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公开(公告)号：KR1020130074292A
公开(公告)日：2013-07-04
申请号：KR1020110142287
申请日：2011-12-26
Applicant: 한국항공우주연구원
Inventor： 박근주
CPC classification number: G08B21/0269 , G08B3/10 , G08B21/0277 , G08B21/0453 , G08B25/10 , G08C17/02
Abstract: PURPOSE: A method for sensing an emergency situation and delivering an alarm and a system are provided to collect and store an accelerometer, global positioning system (GPS) information, pulse and body temperature information which is embedded in a smart phone by integrating a pulsimeter and a thermometer having an application and a blue-tooth function, thereby quickly coping with the emergency situation by transmitting related information to a protector and a relief center. CONSTITUTION: A method for sensing an emergency situation and delivering an alarm comprises a data collection storage step (S100), an emergency situation sensing step (S200), an emergency situation notification step (S300), and a warning tone transmission step (S400). The data collection storage step stores one or more information among pulse information of a user, body temperature information, GPS location information of a smart phone, activity information of a smart phone user. The emergency situation sensing step senses the emergency situation of a user by comparing with stored information with pre-stored reference information. The emergency situation notification step transmits the emergency situation of the user to a predetermined receiving station when the emergency situation of the smart phone user is sensed. The warning tone transmission step transmits warning tone to the smart phone of the user. [Reference numerals] (S100) Store the pulse, body temperature, location, and action information of a user; (S200) Detect an emergency situation; (S300) Warn the emergency situation; (S400) Output an alarming sound from a smart phone
Abstract translation: 目的：提供一种用于感测紧急情况并提供报警和系统的方法，用于通过集成脉搏计和智能手机来收集和存储嵌入在智能手机中的加速度计，全球定位系统（GPS）信息，脉搏和体温信息 具有应用和蓝牙功能的温度计，从而通过将相关信息传送到保护器和救济中心来快速应对紧急情况。 构成：用于感测紧急情况和发送警报的方法包括数据收集存储步骤（S100），紧急情况感测步骤（S200），紧急情况通知步骤（S300）和警告音发送步骤（S400） 。 数据收集存储步骤在用户的脉冲信息，体温信息，智能电话的GPS位置信息，智能电话用户的活动信息之间存储一个或多个信息。 紧急情况检测步骤通过与存储的信息与预先存储的参考信息进行比较来检测用户的紧急情况。 当感测到智能电话用户的紧急情况时，紧急情况通知步骤将用户的紧急情况发送到预定的接收站。 警告音发送步骤向用户的智能电话发送警告音。 （附图标记）（S100）存储用户的脉搏，体温，位置和动作信息; （S200）检测紧急情况; （S300）警告紧急情况; （S400）从智能手机输出警报声
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公开(公告)号：KR100942010B1
公开(公告)日：2010-02-12
申请号：KR1020070140751
申请日：2007-12-28
Applicant: 한국항공우주연구원
IPC: B64G1/22
Abstract: 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-
公开(公告)号：KR1020090072594A
公开(公告)日：2009-07-02
申请号：KR1020070140751
申请日：2007-12-28
Applicant: 한국항공우주연구원
IPC: B64G1/22
Abstract: A cosmic dust injection system for a satellite is provided to heighten profitability because the expendable fuel like propellant is not used. A cosmic dust injection system for a satellite comprises a main body(110) in which cosmic dust is emitted to one opened end, a spring(150) which is inserted into the main body, whereof one end is formed with the jetting surface contacting with the cosmic dust, a screw shaft(120) which is installed in the main body and rotates with the motor, and a fixation pin(130) which compresses and releases the spring.
Abstract translation: 提供用于卫星的宇宙除尘注入系统，以提高利润率，因为不使用消耗性燃料如推进剂。 用于卫星的宇宙粉尘喷射系统包括：主体（110），其中将宇宙尘埃发射到一个开放端;弹簧（150），其插入主体中，其一端形成有与 宇宙尘埃，安装在主体中并与电动机一起旋转的螺杆轴（120）和压缩并释放弹簧的固定销（130）。
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4.发明公开
公开(公告)号：KR1020080003296A
公开(公告)日：2008-01-07
申请号：KR1020070133556
申请日：2007-12-18
Applicant: 한국항공우주연구원
IPC: G01S5/14
Abstract: A method and an apparatus for determining GEO stationary satellite attitude and orbit using multiple ground based GPS signal transceivers are provided to determine the attitude and the position of a GEO stationary satellite using the GPS signal transmitted from the multiple ground based GPS transceivers. According to an apparatus for determining GEO stationary satellite attitude and orbit, a number of ground base stations transmit a GPS signal by being installed on the ground. A number of antennas receive the GPS signal by being installed on a stationary satellite. A calculation part calculates the attitude and orbit of the GEO stationary satellite by analyzing the GPS signal received by the antennas.
Abstract translation: 提供了一种用于使用多个基于地面的GPS信号收发器来确定GEO固定卫星姿态和轨道的方法和装置，以使用从多个基于地面的GPS收发器发送的GPS信号来确定GEO固定卫星的姿态和位置。 根据用于确定GEO固定卫星姿态和轨道的装置，许多地面基站通过安装在地面上传输GPS信号。 许多天线通过安装在固定卫星上来接收GPS信号。 计算部分通过分析由天线接收的GPS信号来计算GEO固定卫星的姿态和轨道。
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Patent Agency Ranking
公开(公告)号：KR101510435B1
公开(公告)日：2015-04-10
申请号：KR1020130136717
申请日：2013-11-12
Applicant: 한국항공우주연구원
Inventor： 박근주
IPC: G05D1/08
CPC classification number: G05D1/0883
Abstract: 본발명은단일차분을이용한 3축각속도센서의오정렬및 축척계수오차보정방법에관한것으로, 더욱상세하게는위성탑재컴퓨터에서결정된자이로표류오차추정값의단일차분(S20)과, 위성에장착된자이로각속도측정값의단일차분(S10)을이용한 3축각속도센서의오정렬및 축척계수오차보정방법에있어서, 상기위성에장착된자이로각속도측정값에대한단일차분결과(S10)값과자이로표류오차추정값의단일차분결과(S20)값을전달하는데이터획득처리단계(S100), 상기데이터획득처리단계(S100)로부터상기위성에장착된자이로각속도측정값에대한단일차분결과(S10)값과자이로표류오차추정값의단일차분결과(S20)값을전달받아, T 행렬및 자이로표류오차단일차분벡터의형태로저장하는데이터저장단계(S200), 상기데이터저장단계(S200)에의해획득한상기위성의적어도세가지의지구지향자세에대한정보들을이용하여, 의사역함수(pseudo inverse)를계산하여, 상기각속도센서의오정렬및 축척계수오차값을산출하는오정렬및 축척계수오차산출단계(S300) 및상기오정렬및 축척계수오차산출단계(S300)에서산출한상기각속도센서의오정렬및 축척계수오차값을이용하여, 상기각속도센서의오정렬및 축척계수를보정하는오차보정단계(S400)로이루어지는것을특징으로하는단일차분을이용한 3축각속도센서의오정렬및 축척계수오차보정방법에관한것이다.
Abstract translation: 本发明涉及一种用于补偿使用单一差异的3轴角速度传感器的未对准和比例因子误差的方法，更具体地说，涉及用于补偿3轴的不对准和比例因子误差的方法 使用由卫星车载计算机确定的陀螺漂移误差估计值的单一差异（S20）和安装在卫星上的陀螺仪的角速度测量值的单一差异（S10）的角速度传感器。 用于补偿使用单一差异的3轴角速度传感器的未对准和比例因子误差的方法包括：数据获取处理步骤（S100），将用于角速度测量值的单个差分结果（S10） 陀螺仪在卫星上沉积，陀螺漂移误差估计值的单一差分结果（S20）值; 数据存储步骤（S200），从数据采集中接收用于安装在卫星上的陀螺仪的角速度测量值的单个差分结果（S10）值和陀螺漂移误差估计值的单一差分结果（S20）值 处理步骤（S100）并以T矩阵和陀螺漂移误差单差矢量的形式存储数据; 通过使用通过数据存储步骤（S200）获取的关于卫星的至少三个地球定向位置的信息来计算伪反函数的未对准和比例因子误差计算步骤（S300），并计算未对准和比例 角速度传感器的因子误差值; 以及误差补偿步骤（S400），其通过使用由所述未对准和比例因子误差计算步骤计算的角速度传感器的未对准和比例因子误差值来补偿角速度传感器的未对准和销售系数（ S300）。
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公开(公告)号：KR1020160073052A
公开(公告)日：2016-06-24
申请号：KR1020140181368
申请日：2014-12-16
Applicant: 한국항공우주연구원
Inventor： 박근주
IPC: B64G1/28
Abstract: 본발명은외란을최소화하는무게중심옵셋을검출하여이동체의무게중심을실시간으로보정할수 있는실시간무게중심옵셋검출을통한능동적무게중심및 관성모멘트제어장치를제공하는것이그 기술적과제이다. 이를위해, 본발명의실시간무게중심옵셋검출을통한능동적무게중심및 관성모멘트제어장치는, 무게중심이동유닛을포함하는이동체에대한실시간무게중심옵셋검출을통한능동적무게중심및 관성모멘트제어장치로, 상기이동체에구비되며상기이동체의각속도를측정하는센서부; 상기센서부를통해측정되는각속도를이용하여추력벡터와무게중심사이의옵셋거리를실시간으로연산하는연산부; 및상기무게중심이동유닛을제어하여상기연산된옵셋거리만큼상기이동체의무게중심을실시간으로보정하는제어부를포함한다.
Abstract translation: 本发明提供了一种通过检测重心偏移实时检测重心偏移来实时控制主动重心和惯性力的装置和方法，能够通过检测重心的偏移来实时校正运动物体的重心 ，这使干扰最小化。 根据本发明，通过检测重心的偏移来实时检测重心的偏移来控制主动重心和惯性力矩的装置是通过检测重心的偏移来控制主动重心和惯性力的装置 在包括重心移动单元的移动体上实时。 用于通过实时检测重心的偏移来控制主动重心和惯性力的装置包括：测量移动体的角速度并安装在移动体中的传感器单元; 计算单元，通过使用由所述传感器单元测量的角速度实时地计算推力矢量与所述重心之间的偏移距离; 以及控制单元，通过控制重心移动单元，实时地校正移动体的重心与偏移距离一样大。
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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
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。
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公开(公告)号：KR101294623B1
公开(公告)日：2013-08-08
申请号：KR1020120157528
申请日：2012-12-28
Applicant: 한국항공우주연구원
CPC classification number: G05D1/0883 , B64G2001/1057
Abstract: PURPOSE: An enhanced ground based precise posture determination method of a low-orbit imaging satellite is provided to accurately determine the posture of the satellite by dually using gyro measurement data and star tracker measurement data. CONSTITUTION: Gyro measurement data and star tracker measurement data are obtained in different intervals through a gyro sensor and a star tracker using a dual MIL-STD-1553 bus communication device (S100). The gyro measurement data and the star tracker measurement data are stored and transmitted to a ground station (S200). A posture quaternion estimated value is repeatedly predicted until the star tracker measurement data is received after calculating an angular speed by restoring the transmitted gyro measurement data again (S300). A modified value is calculated by using the posture quaternion estimated value and the star tracker measurement data, and an error posture quaternion is applied as a corrected value by using the modified value (S400). [Reference numerals] (S100) Measured data obtaining step; (S200) Measured data transmitting step; (S300) Angular speed calculating and predicting step; (S400) Correcting step
Abstract translation: 目的：提供低轨道成像卫星的基于地面的精确姿态确定方法，通过双重使用陀螺仪测量数据和星形跟踪测量数据来准确地确定卫星的姿势。 构成：通过使用双MIL-STD-1553总线通信装置的陀螺传感器和星形跟踪器，以不同的间隔获得陀螺测量数据和星形跟踪器测量数据（S100）。 陀螺测量数据和星形跟踪测量数据被存储并发送到地面站（S200）。 通过再次恢复发送的陀螺仪测量数据计算角速度之后，重复地预测姿态四元数估计值，直到接收到星形跟踪器测量数据（S300）。 通过使用姿态四元数估计值和星形跟踪器测量数据来计算修改值，并且通过使用修改值将错误姿态四元数作为校正值应用（S400）。 （附图标记）（S100）测量数据获取步骤; （S200）测量数据发送步骤; （S300）角速度计算和预测步骤; （S400）校正步骤
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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。
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