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公开(公告)号：KR101807431B1
公开(公告)日：2017-12-12
申请号：KR1020160128839
申请日：2016-10-06
Applicant: 한국항공우주연구원
Abstract: 결정된제어조건에따라위성체의요우각을제어하고, 태양전지판의회전각을제어하는위성체의제어장치가제공된다. 상기위성체의제어장치는제어조건에따라상기위성체의지향방향을중심으로요우스티어링을수행하여상기위성체의요우각을제어하는제1 제어부및 상기제어조건에따라상기위성체의태양전지판을미리지정된회전축을중심으로회전시켜상기태양전지판의회전각을제어하는제2 제어부를포함할수 있다.
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公开(公告)号：KR101688331B1
公开(公告)日：2016-12-20
申请号：KR1020150148893
申请日：2015-10-26
Applicant: 한국항공우주연구원
CPC classification number: B64G1/365 , G05D1/0094 , G05D1/0883
Abstract: 이동위성체의요우각 변화를센싱하고, 요우각에따른그라운드샘플거리를계산하는제어장치가제공된다. 상기이동위성체의제어장치는상기이동위성체의요우스티어링에상응하는요우각을센싱하는센싱부및 상기이동위성체에의해촬영된픽셀의길이가상기요우각에따라지표면에사영된그라운드샘플거리를계산하는프로세서를포함할수 있다.
Abstract translation: 提供了一种用于通过感测轨道卫星的偏航角的变化并基于偏航角计算地面采样距离（GSD）来控制轨道卫星的装置。 该装置可以包括被配置为感测对应于轨道卫星的偏转转向的偏航角的传感器，以及被配置为基于偏航角计算与投影到行星表面上的像素的长度相对应的GSD的处理器 轨道卫星。
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公开(公告)号：KR101357488B1
公开(公告)日：2014-02-03
申请号：KR1020120112322
申请日：2012-10-10
Applicant: 한국항공우주연구원
Abstract: The present invention relates to an auxiliary test device for a thermostat for a continuity check test of a harness for controlling a heater and to a method for applying the same. More specifically, the present invention relates to an auxiliary test device for a thermostat for a continuity check test allowing a thermostat to act as a switch in a heater control manner of supplying heat to protect a satellite in a low temperature state of a space orbit, which is a representative heat control manner and is configured by a heater, a thermostat, a power supply device and a harness connected therebetween, so that a heater can be operated in a certain temperature range and being capable of inspecting abnormality of entire connection after mounting the device in the satellite, and to a method for applying the same. The auxiliary test device for a thermostat for a continuity check test of a harness for controlling a heater comprises a protection cover which has space formed therein to cover a thermostat in the space; and a coolant container which has a hole of a bigger size than the thermostat in the bottom surface so that the thermostat can be located in the hole and supplies coolant to coolant space between the protection cover and the side surface by connecting the bottom surface to the protection cover.
Abstract translation: 本发明涉及用于控制加热器的线束的连续性检查试验用恒温器的辅助试验装置及其应用方法。 更具体地，本发明涉及一种用于连续性检查测试的恒温器的辅助测试装置，其允许恒温器以加热器控制方式充当开关，以保护在空间轨道的低温状态下的卫星， 这是代表性的热控制方式，并且由加热器，恒温器，电源装置和连接在其间的线束构成，使得加热器可以在一定温度范围内操作并且能够在安装之后检查整个连接的异常 卫星中的设备，以及应用它的方法。 用于控制加热器的线束的连续性检查测试的恒温器的辅助测试装置包括：保护盖，其具有形成在其中的空间以覆盖该空间中的恒温器; 以及冷却剂容器，其具有比底表面中的恒温器大的尺寸的孔，使得恒温器可以位于孔中，并且通过将底表面连接到保护盖和侧表面之间将冷却剂供应到保护盖和侧表面之间的冷却剂空间 防护罩。
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公开(公告)号：KR1020130068134A
公开(公告)日：2013-06-25
申请号：KR1020110135664
申请日：2011-12-15
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A protection device for supplying power is provided to maintain the output of a constant voltage source even in case a high power short period load is connected to the constant voltage source. CONSTITUTION: A protection device for supplying power comprises a diode(120) which blocks a reverse current flow by connecting to a forward direction in an output terminal of a constant voltage source(10); a battery(110) which supplies electricity, charged by using electricity supplied from the constant voltage source with connecting the constant voltage source and a cathode terminal of a diode, to a load(20) with a discharge; and a switching element(140) which is connected between the load and an access node of the diode and the battery and which switches a current flow. [Reference numerals] (130) Current limiter; (20) Load
Abstract translation: 目的：提供一种用于供电的保护装置，即使在高功率短时间负载连接到恒压源的情况下也能保持恒定电压源的输出。 构成：用于供电的保护装置包括：二极管（120），其通过连接到恒定电压源（10）的输出端子中的正向阻挡反向电流; 电池（110），其通过使用从所述恒定电压源供给的电力将所述恒定电压源和二极管的阴极端子连接到具有放电的负载（20）而进行充电; 以及开关元件（140），其连接在负载和二极管和电池的接入节点之间并切换电流。 （附图标记）（130）限流器; （20）负载
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公开(公告)号：KR1020100067734A
公开(公告)日：2010-06-22
申请号：KR1020080126253
申请日：2008-12-12
Applicant: 한국항공우주연구원
Abstract: PURPOSE: An antenna fixing device and an antenna supporting device using the same are provided to easily attach/detach an antenna and convert a direction of the antenna, thereby shortening installation time of the antenna. CONSTITUTION: An antenna fixing device(100) comprises a fixing tool(110) and a coupling device unit(150) for combining the fixing tool. An inserting hole(110b) is formed in the center area of the fixing tool. The fixing tool is classified into an upper fixing unit(111) and a lower fixing unit(113) around the inserting hole. The coupling device unit comprises a lower support(153) and an upper cover(151). One end of the lower support and one end of the upper cover are combined with a hinge(155).
Abstract translation: 目的：提供天线固定装置和使用该天线固定装置的天线支撑装置，以容易地安装/拆卸天线并转换天线的方向，从而缩短天线的安装时间。 构成：天线固定装置（100）包括用于组合固定工具的固定工具（110）和联接装置单元（150）。 插入孔（110b）形成在固定工具的中心区域。 固定工具分为上部固定单元（111）和下部固定单元（113）围绕插入孔。 联接装置单元包括下支撑件（153）和上盖板（151）。 下支撑件的一端和上盖的一端与铰链（155）组合。
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Patent Agency Ranking
公开(公告)号：KR1020020081619A
公开(公告)日：2002-10-30
申请号：KR1020010021019
申请日：2001-04-19
Applicant: 한국항공우주연구원
IPC: H04L27/18
CPC classification number: H04L27/18
Abstract: PURPOSE: A dual communication speed adaptive baseband switching phase shift keying apparatus is provided, which can perform a phased verification between switch modules by providing a bypass path between switch modules, and can perform an accurate test using a low pass filter and a band pass filter. CONSTITUTION: A baseband control apparatus(4) is constituted so that it receives a baseband signal input from a baseband signal processing apparatus(1) and a ranging signal a simulated remote control command signal from a waveform generation apparatus(2) and then applies them to a upward modulation apparatus(5), and provides a signal made by demodulating an RF signal received from a satellite in a downward demodulation apparatus(6) to a frequency counter(3) and on the other hand applies a part of the demodulated signal to the baseband signal processing apparatus.
Abstract translation: 目的：提供双通道速度自适应基带切换相移键控装置，通过提供交换机模块之间的旁路，可以对交换机模块之间进行相位验证，并可使用低通滤波器和带通滤波器 。 构成：基带控制装置（4）构成为从波形生成装置（2）接收从基带信号处理装置（1）输入的基带信号和测距信号，模拟的遥控指令信号，然后施加它们 向上调制装置（5）提供通过将从下行解调装置（6）中的卫星接收的RF信号解调成频率计数器（3）而得到的信号，另一方面，施加部分解调信号 到基带信号处理装置。
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公开(公告)号：KR1020000045958A
公开(公告)日：2000-07-25
申请号：KR1019980062608
申请日：1998-12-30
Applicant: 한국항공우주연구원
IPC: H04B17/00
CPC classification number: H04B17/0082 , G06F11/2733
Abstract: PURPOSE: A serial signal communication apparatus is provided to achieve serial signal communication so that a ground performance test equipment can perform the relay control supply and status signal confirmation of a satellite power control unit. CONSTITUTION: A locking signal generation unit(50) generates a locking signal delaying a specific time to confirm a relay status. A locked clock signal generation unit(60) generates a locked clock signal by the locking signal of the locking signal generation unit(50). A shift register(20) shifts the relay control signal of a VXI bus(10) into the locked clock signal of the locked clock signal generation unit(60). A parity bit generation unit(30) generates the parity bit in the serial signal of the shift register(20) to supply to a satellite power control unit(40). A shift register(70) shifts the relay status confirmation signal of the satellite power control unit(40) into a parallel signal. A parity bit confirmation unit(80) supplies the parity bit comprised in the parallel signal of the shift register(70) to the VXI bus(10).
Abstract translation: 目的：提供串行信号通信装置以实现串行信号通信，使得地面性能测试设备可以执行卫星功率控制单元的继电器控制电源和状态信号确认。 构成：锁定信号生成单元（50）产生延迟特定时间以确认中继状态的锁定信号。 锁定时钟信号生成单元（60）通过锁定信号生成单元（50）的锁定信号产生锁定的时钟信号。 移位寄存器（20）将VXI总线（10）的继电器控制信号移动到锁定时钟信号生成单元（60）的锁定时钟信号。 奇偶校验位生成单元（30）生成移位寄存器（20）的串行信号中的奇偶校验位，供给卫星功率控制单元（40）。 移位寄存器（70）将卫星功率控制单元（40）的中继状态确认信号移动为并行信号。 奇偶校验位确认单元（80）将包括在移位寄存器（70）的并行信号中的奇偶校验位提供给VXI总线（10）。
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公开(公告)号：KR101806402B1
公开(公告)日：2017-12-07
申请号：KR1020160075712
申请日：2016-06-17
Applicant: 한국항공우주연구원
CPC classification number: B64G1/36 , B64G1/1021 , B64G2001/1028 , B64G2001/245 , B64G1/24 , B64G1/66 , G05D1/08
Abstract: 인공위성을제어하는방법및 컴퓨터판독가능한기록매체가개시된다. 본발명의다양한실시예에따른인공위성을제어하는방법은, 적도면과경사각을갖는궤도로회전하는인공위성이정북방향의영상을촬영하도록인공위성을제어하는방법에있어서, 상기인공위성의위치를판단하는단계, 촬영점인제1 지표면으로상기인공위성의시선벡터가향하기위한상기인공위성의롤각과피치각을산출하는단계, 상기촬영점에대한정북방향의영상을촬영하기위한보상각을결정하는단계, 상기보상각에기초하여요(yaw)각을산출하는단계, 및상기산출된롤(Roll)각, 상기산출된피치(Pitch)각및 상기산출된요(yaw)각에따라상기인공위성을회전시키는단계를포함한다.
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公开(公告)号：KR101363697B1
公开(公告)日：2014-02-17
申请号：KR1020110135664
申请日：2011-12-15
Applicant: 한국항공우주연구원
Abstract: 본 발명은 전원공급 보호장치에 관한 것으로, 정전압원과 부하 사이에 개재되어 상기 부하에 정전압이 공급되도록 하는 전원공급 보호장치에 있어서, 상기 정전압원의 출력단에 순방향 접속되어 역방향 전류 흐름을 차단하는 다이오드와; 상기 다이오드의 캐소드 단자와 상기 정전압원 사이에 접속되어 상기 정전압원으로부터 공급되는 전력을 이용하여 충전되고, 충전된 전력을 상기 부하로 방전 공급하는 배터리; 및 상기 다이오드와 상기 배터리의 접속 노드와 상기 부하 사이에 접속되어 전류 흐름을 스위칭하는 스위칭소자를 포함한다.
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