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公开(公告)号：KR1020090058299A
公开(公告)日：2009-06-09
申请号：KR1020070125018
申请日：2007-12-04
Applicant: 한국항공우주연구원
IPC: G02B23/00
CPC classification number: G02B23/165 , G02B7/183 , G02B27/0025
Abstract: A method for correcting a sensor of a satellite optical telescope by a random exposure time control is provided to correct a sensor of a satellite optical telescope without a separate constraint condition about an input light source and an operation mode. An exposure time of a detector of a satellite optical telescope is controlled according to a Gaussian random distribution. A nonlinear model equation of the satellite optical telescope is induced. The nonlinear model equation is classified into a mean value and a random variable. The random variable is converted into a PDF(Power Density Function). A chi-square distribution is obtained by performing an addition/average filter in the converted PDF. The obtained chi-square distribution is transformed. Two nonlinear equations including linear and non linear values are induced by a maximum-likelihood method. A sensor of the satellite optical telescope is corrected through the linear and non linear values.
Abstract translation: 提供了一种通过随机曝光时间控制来校正卫星光学望远镜的传感器的方法，以在没有关于输入光源和操作模式的单独约束条件下校正卫星光学望远镜的传感器。 根据高斯随机分布来控制卫星光学望远镜的探测器的曝光时间。 引入卫星光学望远镜的非线性模型方程。 非线性模型方程分为平均值和随机变量。 随机变量被转换为PDF（功率密度函数）。 通过在转换的PDF中执行加法/平均滤波器来获得卡方分布。 获得的卡方分布被转换。 包括线性和非线性值的两个非线性方程由最大似然法引发。 卫星光学望远镜的传感器通过线性和非线性值进行校正。
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公开(公告)号：KR1020070067929A
公开(公告)日：2007-06-29
申请号：KR1020050129467
申请日：2005-12-26
Applicant: 한국항공우주연구원
IPC: H04N5/238
CPC classification number: H04N5/238 , G03B17/565
Abstract: A system for radiometric-calibrating a geostationary orbit electro-optical camera is provided to reflect sun's rays and input the reflected sun's rays to an input port of the electro-optical camera to measure characteristics of the electro-optical camera by using the sun's rays as a source without changing the posture of a satellite. A system for radiometric-calibrating a geostationary orbit electro-optical camera includes a directing unit(110) and a pointing reflector(120). The directing unit reflects sun's rays to direct the sun's rays to a predetermined direction. The pointing reflector reflects the sun's rays projected from the directing unit such that the sun's rays are inputted to the electro-optical camera. The characteristics of the electro-optical camera are measured without changing the posture of the electro-optical camera.
Abstract translation: 提供用于辐射校准对地静止轨道电光学照相机的系统以反射太阳光并将反射的太阳光线输入到电光学相机的输入端口，以通过使用太阳光线来测量电光学相机的特性 一个来源，而不改变卫星的姿势。 用于辐射校准对地静止轨道电光学照相机的系统包括导向单元（110）和指示反射器（120）。 引导单元反射太阳的光线以将太阳的光线引导到预定的方向。 指示反射器反射从定向单元投影的太阳的光线，使得太阳的光线被输入到电光学照相机。 在不改变电光学摄像机的姿势的情况下测量电光学相机的特性。
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公开(公告)号：KR1020060077387A
公开(公告)日：2006-07-05
申请号：KR1020040116231
申请日：2004-12-30
Applicant: 한국항공우주연구원
CPC classification number: B64G1/1021 , B64G2001/1042 , H04N5/52
Abstract: 본 발명은 위성 해양관측 탑재체의 고정밀 이중이득 시스템에 관한 것으로, 해양 영상을 측정하는 2개의 검지기와; 상기 각각의 검지기로부터 측정된 영상데이터가 입력되는 고이득 장치 및 저이득 장치와; 상기 각각의 이득 장치의 출력신호를 디지털신호로 변환하여 출력하는 A/D 변환기; 및 상기 고이득 장치의 출력값과 설정된 기준 포화값을 비교하여 상기 출력값이 기준 포화값 이상일 때는 저이득 데이터가 선택되게 하고, 기준 포화값 이하일 때는 고이득 데이터가 선택되게 하는 비교기로 이루어진다. 이러한 본 발명의 구성에 의해 해양 영상의 정밀한 측정이 가능함과 아울러 위성 해양관측 탑재체의 전력소모를 적게하고, 그 크기를 축소시킬 수 있다.
위성, 해양관측, 탑재체, 이중이득, 검지기, 비교기-
公开(公告)号：KR1020040026948A
公开(公告)日：2004-04-01
申请号：KR1020020058603
申请日：2002-09-27
Applicant: 한국항공우주연구원
IPC: B64G1/50
Abstract: PURPOSE: A thermal control method to improve stability of a satellite load thermal control system is provided to secure stable working of load or a satellite bus by executing thermal control by a predetermined temperature and a heater timetable and executing thermal control by a thermostat in substitute for a temperature control loop although the temperature control loop is broken down. CONSTITUTION: A thermal control method to improve stability of a satellite load thermal control system comprises steps of collecting temperature data(309) by a CPU(Central Processing Unit,315) of a thermal control part from a temperature sensor group installed to a thermal control target system, in executing normal thermal control; comparing the data with a heater ON/OFF reference temperature value set up to a temperature table(306) and then controlling a heater(302) by turning a switch(312) ON/OFF through an optical coupler(313), if an ON/OFF bit command is given to a buffer(314); controlling the heater by the period of heater ON/OFF time of a timetable(316), in executing thermal control when a temperature sensor of the temperature sensor group is broken down; and executing thermal control by installing a thermostat(317) having a wide temperature control range.
Abstract translation: 目的：提供一种提高卫星负载热控制系统稳定性的热控制方法，以通过执行预定温度和加热器时间表的热控制并通过恒温器进行热控制来确保负载或卫星总线的稳定工作，代替 温度控制回路虽然温度控制回路被分解。 构成：用于提高卫星负载热控制系统的稳定性的热控制方法包括以下步骤：将热控制部件的CPU（中央处理单元，315）从安装到热控制器的温度传感器组收集温度数据（309） 目标系统，正常热控制; 将数据与设置到温度表（306）的加热器ON / OFF参考温度值进行比较，然后通过光耦合器（313）打开/关闭开关（312）来控制加热器（302），如果ON / OFF位命令被赋予缓冲器（314）; 当温度传感器组的温度传感器被分解时，执行热控制，在时间表（316）的加热器ON / OFF时间周期内控制加热器; 并通过安装具有宽温度控制范围的恒温器（317）来执行热控制。
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公开(公告)号：KR100400976B1
公开(公告)日：2003-10-10
申请号：KR1020000074567
申请日：2000-12-08
Applicant: 한국항공우주연구원
IPC: G05B19/408
Abstract: PURPOSE: A method of controlling a data storage device for extending a realtime observation range of a satellite is provided to control a data reading operation and a data writing operation by comparing a data reading position with a data writing position. CONSTITUTION: A low-orbit ground observation satellite has a compressing function(102) of observation data. A reading end time of storing data is set up in order to extend a ground observation range of the low-orbit ground observation satellite(202). The observation data are stored in a storage device(201). A data writing function is finished if a writing position of data corresponds to a reading position of data(203,204). A data reading operation and a data transmission operation of the storage device are performed until the reading end time(205-207) after the data writing function is finished. The data are stored in the storage device and the data reading operation and the data transmission operation of the storage device are performed until the reading end time(205-207) if the writing position of data does not corresponds to the reading position of data(203).
Abstract translation: 目的：提供一种控制用于扩展卫星的实时观测范围的数据存储装置的方法，以通过比较数据读取位置和数据写入位置来控制数据读取操作和数据写入操作。 构成：低轨道地面观测卫星具有观测数据的压缩功能（102）。 为了扩展低轨道地面观测卫星（202）的地面观测范围，设置了存储数据的读取结束时间。 观测数据被存储在存储装置（201）中。 如果数据的写入位置对应于数据的读取位置（203,204），则完成数据写入功能。 执行存储设备的数据读取操作和数据传输操作，直到数据写入功能完成之后的读取结束时间（205-207）。 数据被存储在存储装置中，并且如果数据的写入位置不对应于数据的读取位置，则执行存储装置的数据读取操作和数据传输操作，直到读取结束时间（205-207） 203）。
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Patent Agency Ranking
公开(公告)号：KR1020020045197A
公开(公告)日：2002-06-19
申请号：KR1020000074567
申请日：2000-12-08
Applicant: 한국항공우주연구원
IPC: G05B19/408
Abstract: PURPOSE: A method of controlling a data storage device for extending a realtime observation range of a satellite is provided to control a data reading operation and a data writing operation by comparing a data reading position with a data writing position. CONSTITUTION: A low-orbit ground observation satellite has a compressing function(102) of observation data. A reading end time of storing data is set up in order to extend a ground observation range of the low-orbit ground observation satellite(202). The observation data are stored in a storage device(201). A data writing function is finished if a writing position of data corresponds to a reading position of data(203,204). A data reading operation and a data transmission operation of the storage device are performed until the reading end time(205-207) after the data writing function is finished. The data are stored in the storage device and the data reading operation and the data transmission operation of the storage device are performed until the reading end time(205-207) if the writing position of data does not corresponds to the reading position of data(203).
Abstract translation: 目的：提供一种控制用于扩展卫星的实时观察范围的数据存储装置的方法，以通过将数据读取位置与数据写入位置进行比较来控制数据读取操作和数据写入操作。 构成：低轨道地面观测卫星具有观测数据的压缩函数（102）。 设置存储数据的读取结束时间，以便扩展低轨道地面观测卫星（202）的地面观测范围。 观察数据存储在存储装置（201）中。 如果数据的写入位置对应于数据的读取位置（203,204），则完成数据写入功能。 执行存储装置的数据读取操作和数据传输操作，直到数据写入功能完成之后的读取结束时间（205-207）。 数据被存储在存储装置中，并且如果数据的写入位置不对应于数据的读取位置，则执行存储装置的数据读取操作和数据传输操作直到读取结束时间（205-207） 203）。
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公开(公告)号：KR100286521B1
公开(公告)日：2001-04-16
申请号：KR1019970042689
申请日：1997-08-29
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A method for transmitting exploratory data in a remote exploration satellite is provided to effectively transmit mass exploratory data by setting a geostationary satellite orbit transmission path composed as a transponder of the geostationary satellite orbit and transmitting the exploratory data. CONSTITUTION: An exploratory data transmitting device(202) transmits exploratory data corresponding to the transmission capacity of a wireless transmission path(203) through the wireless transmission path(203). The exploratory data transmitting device(202) transmits exploratory data which are over the transmission capacity of the wireless transmission path(203) through a geostationary satellite orbit transmission path(205) via a transponder of a geostationary orbit relay satellite.
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公开(公告)号：KR100777423B1
公开(公告)日：2007-11-20
申请号：KR1020050129467
申请日：2005-12-26
Applicant: 한국항공우주연구원
IPC: H04N5/238
Abstract: 본 발명의 정지궤도 전자광학카메라 보정시스템은, 입사되는 태양광을 일정한 방향으로 지향하도록 반사시켜 상기 전자광학카메라의 입력단으로 입사시킴으로써, 위성체의 자세 변경없이 태양광을 소스로 하여 상기 전자광학카메라의 특성 측정할 수 있는 보정시스템에 관한 것이다.
본 발명은, ① 태양으로부터 입사되는 태양광을 일정한 방향으로 지향되도록 경로를 반사하여 투사하는 지향체와, ② 상기 지향체로부터 출사된 태양광을 상기 전자광학카메라로 입사되도록 포인트를 맞추어 반사시키는 포인팅반사체를 구비하고 있다.
따라서 본 발명은 정지궤도의 전자광학카메라를 위성체 자세제어 없이 태양광원을 이용하여 그 특성을 측정할 수 있어, 자세 변경 등에 따른 연료소모 및 수명단축의 문제를 남기지 않는 상태로, 측정의 결과를 보정 등을 위한 다양한 용도로 활용할 수 있는 효과를 제공한다.
정지궤도, 위성, 해양관측, 탑재체, 태양광원, 보정-
公开(公告)号：KR100442708B1
公开(公告)日：2004-08-02
申请号：KR1020020058603
申请日：2002-09-27
Applicant: 한국항공우주연구원
IPC: B64G1/50
Abstract: PURPOSE: A thermal control method to improve stability of a satellite load thermal control system is provided to secure stable working of load or a satellite bus by executing thermal control by a predetermined temperature and a heater timetable and executing thermal control by a thermostat in substitute for a temperature control loop although the temperature control loop is broken down. CONSTITUTION: A thermal control method to improve stability of a satellite load thermal control system comprises steps of collecting temperature data(309) by a CPU(Central Processing Unit,315) of a thermal control part from a temperature sensor group installed to a thermal control target system, in executing normal thermal control; comparing the data with a heater ON/OFF reference temperature value set up to a temperature table(306) and then controlling a heater(302) by turning a switch(312) ON/OFF through an optical coupler(313), if an ON/OFF bit command is given to a buffer(314); controlling the heater by the period of heater ON/OFF time of a timetable(316), in executing thermal control when a temperature sensor of the temperature sensor group is broken down; and executing thermal control by installing a thermostat(317) having a wide temperature control range.
Abstract translation: 目的：提供一种改善卫星负载热控制系统稳定性的热控制方法，以通过执行预定温度和加热器时间表的热控制并通过恒温器执行热控制代替以确保负载或卫星总线的稳定工作 一个温度控制回路，尽管温度控制回路被分解。 本发明提供了一种改善卫星负载热控制系统稳定性的热控方法，包括以下步骤：由热控制部件的CPU（中央处理单元，315）从安装到热控制器的温度传感器组收集温度数据（309） 目标系统执行正常的热控制; 将该数据与设定为温度表（306）的加热器开/关参考温度值进行比较，然后通过经由光耦合器（313）接通/断开开关（312）来控制加热器（302），如果ON / OFF位命令被提供给缓冲器（314）; 在温度传感器组的温度传感器发生故障时执行热控制;在时间表的加热器开/关时间周期内控制加热器（316）;当温度传感器组的温度传感器发生故障时执行热控制; 并通过安装具有宽温度控制范围的恒温器（317）来执行热控制。
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