| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | 위성 운영 시스템 | KR1020150114474 | 2015-08-13 | KR101631856B1 | 2016-06-20 | 천이진 |
| 본발명은위성운영시스템에관한것으로, 본발명에따른시스템은인가되는제1 제어신호에따라스위칭동작하여전원공급버스를제1 전원공급라인을통해제1 컴퓨터와연결시키거나전원공급버스를백업전원공급라인을통해제1 컴퓨터와연결시키는제1 스위칭릴레이, 인가되는제2 제어신호에따라스위칭동작하여전원공급버스를제2 전원공급라인을통해제2 컴퓨터에연결시키거나전원공급버스를백업전원공급라인을통해제2 컴퓨터에연결시키는제2 스위칭릴레이, 그리고인가되는제3 제어신호에따라스위칭동작하여전원공급버스를백업전원공급라인을통해제1 컴퓨터에연결시키거나전원공급버스를백업전원공급라인을통해제2 컴퓨터에연결시키는백업스위칭릴레이를포함한다. | ||||||
| 82 | 인공위성용 힌지 장치 | KR1020080007065 | 2008-01-23 | KR100942172B1 | 2010-02-12 | 박희창; 김병인; 이성휘; 김진희; 김경원; 김선원; 김규선; 진익민; 이상률; 이주진 |
| 본 발명은 인공위성용 힌지 장치에 관한 것으로서, 더욱 상세하게는 우주공간의 극한환경(극 고온, 극저온현상)에서도 인공위성에서 태양전지판이 원활히 전개되고, 인공위성이 우주선에 실려 우주로 쏘아 올려질 때 발생되는 진동에도 잘 견디며, 상기 태양전지판의 완전 전개되어 우주공간에서 비행시, 발생되는 진동 및 충격 등에도 잘 견디는 특징이 있다. 이와 같이, 본 발명은 우주공간의 극한환경에서도 태양전지판이 전개되도록 인공위성과 태양전지판을 연결하거나 태양전지판과 태양전지판을 연결하는 힌지부에 있어서, 상기 인공위성 또는 태양전지판의 일단부에 결합부재에 의해 부착되는 제 1플레이트와; 상기 태양전지판의 일단부에 결합부재에 의해 부착되되, 상기 제 1플레이트와 끝단부가 축에 의해 결합되어 태양전지판을 전개시키는 제 2플레이트와; 상기 제 1플레이트와 제 2플레이트에 상호 연결되어 제 1플레이트와 제 2플레이트를 탄성적으로 전개되도록 형성된 인장 스프링을 포함하여 구성되는 것을 특징으로 하는 특징이 있다. 인공위성, 태양전지판, 힌지장치, 플레이트, 인장 스프링 | ||||||
| 83 | 다단계태양전지판 인공위성[크니인공위성] | KR1020000005675 | 2000-02-07 | KR1020010077700A | 2001-08-20 | 김남영 |
| PURPOSE: An artificial satellite is provided to effectively supply power, to increase the durability and to lengthen a life of the artificial satellite. CONSTITUTION: Many solar battery plates are prepared inside a sealing box to be insulated from radioactivity. In finishing a life of the initially unfolded solar battery plate, the stood-by solar battery plates are unfolded sequentially. By continuously lengthening a life of an artificial satellite, power is not lack. In leaking the power supply by reducing the efficiency of the solar battery plate, the new solar battery plate is pushed from a main body of the artificial satellite to supplement the power. | ||||||
| 84 | SATELLITE ARTIFICIEL | EP16763906.1 | 2016-08-10 | EP3259188A1 | 2017-12-27 | CAEL, Philippe; WALKER, Andrew; MENA, Fabrice |
| The invention concerns an artificial satellite comprising one face from the North face and the South face supporting at least one main radiator (42, 44) having an outer face turned towards space and an inner face opposite the outer face. The satellite comprises a bearing structure carrying the North face, the South face, the East face and the West face. At least one part (54, 56) of said at least one main radiator (42, 44) protrudes from at least one face from the East face and the West face (36). The inner face of said at least one protruding part (54, 56) is covered with a high infrared emissivity material. The value of the dimension (L54,56) of said at least one protruding part (54, 56) is between 19% and 50% of the value of the distance (Lc) between the East and West faces. | ||||||
| 85 | 인공위성용 항법 장치 | KR1020080017794 | 2008-02-27 | KR1020090092510A | 2009-09-01 | 장영근; 최영훈 |
| A navigation device for an artificial satellite is provided to improve the performance of whole system by processing the sensing data distributionally. A navigation device for an artificial satellite comprises a sensor unit(101), a main processor(102), and an interface unit(103). The sensor unit makes the sensing data by measuring the state of the location or the posture of an antibody. The main processor performs the navigation calculation using the sensing data. The interface unit provides an interface between the main processor and the sensor unit. Sensing data is filtered by the interface unit using the predetermined controller. The interface unit temporarily stores the sensing data of the sensor unit and delivers to the main processor once request. | ||||||
| 86 | 무조정 가능한 인공위성용 안테나 | KR1020010036566 | 2001-06-26 | KR1020030000539A | 2003-01-06 | 정만영 |
| PURPOSE: A non-adjustable artificial satellite antenna is provided to smoothly perform communication between the fixed or mobile station and artificial satellite by radiating, in all directions, high gain narrow band beam having angle of 45 degrees with respect to the receiving/transmitting point of receiver/transmitter equipment. CONSTITUTION: A non-adjustable artificial satellite antenna comprises a circular cone(1) having diameter(D) and length(L), and which tunes waves output from a circular reflector mirror(2) and an outer conductor in accordance with the resonance frequency and radiates beams for communication with the artificial satellite in circularly polarized waves or vertically polarized waves; the circular reflector mirror having a diameter(d), and which is disposed to be opposed to the external conductor of the circular cone, and outputs waves input through a coaxial cable(3) to the external conductor of the circular cone; and the coaxial cable having a central conductor connected to the circular cone and an outer conductor connected to the circular reflector mirror, wherein the coaxial cable is connected to a receiver/transmitter equipment arranged on the ground, and outputs waves for communication with the artificial satellite to the circular cone and the circular reflector mirror. | ||||||
| 87 | 인공위성을 이용한 인터넷 방송 시스템 | KR1020010022407 | 2001-04-25 | KR1020020082683A | 2002-10-31 | 장영삼 |
| PURPOSE: An Internet broadcasting system using an artificial satellite is provided to reduce usage of the Internet and a router by realizing a unicast using an IP multicast which uses an artificial satellite as a local server. CONSTITUTION: The first Internet site(20) includes a multicast(21), a web server(22), a hub(23), and an encoder(24). An artificial satellite(30) receives a multicast signal from the encoder(24) and outputs a corresponding signal. The second Internet site(40) includes a central distribution server(41), a web server(42), a hub(43), and a decoder(44). Telephone offices(50-70) comprise local remote distribution servers(51-53)(61-63)(71-73) which receive a multicast signal from the second Internet site(40). An ADSL router(80) receives a signal from the telephone office(50) as a unicast, performs a switching of the signal, and transmits the signal to a user(110). A cable modem(90) receives a signal from the telephone office(60) as a unicast and transmits the signal to a user(120). A private line(100) receives a signal from the telephone office(70) and transmits the signal to a user(130). | ||||||
| 88 | 인공위성 중계기내 ＲＦ 송신장치 | KR1019990047211 | 1999-10-28 | KR1020010039006A | 2001-05-15 | 이무홍; 허원혁 |
| PURPOSE: An RF transmitting apparatus in an artificial satellite repeater is provided to make a compact size of an RF transmitting apparatus by implementing a circuit by using a single temperature compensating variable amplifier, and reduce a production cost and shorten a production term as production processes are reduced by implementing the whole components in a single metal housing. CONSTITUTION: An attenuator(1000) receives a 10GHz extreme high frequency(EHF) signal from a front block, attenuates the amplitude of the signal to a proper level, and outputs it to a multiplier(2000). The multiplier(2000) receives the 10GHz EHF signal from the attenuator(1000), multiplies the frequency of the 10GHz EHF signal and outputs it to a band-pass filter(3000). The band-pass filter(3000) receives a 20GHz EHF signal from the multiplier(2000), filters it to pass only a desired frequency band of the 20GHz EHF signal and outputs it to a variable attenuator(4000). When an attenuation set level is determined according to a user's selection, the variable attenuator(4000) receives the 20GHz EHF signal from the band-pass filter(3000), attenuates the amplitude of the EHF signal corresponding to the attenuation set level, and outputs it to a three-step variable amplifier(6000). A temperature compensation driving circuit(5000) measures a temperature of an artificial satellite repeater, and outputs a corresponding temperature compensation control voltage to the three-step variable amplifier(6000). The three-step variable amplifier(6000) of which an amplification level is adjusted by the temperature compensation control voltage outputted from the temperature compensation driving circuit(5000), receives the 20GHz EHF signal from the variable attenuator(4000) and amplifies the amplitude of the 20GHz EHF signal to a proper level. | ||||||
| 89 | 一种利用和差波束天线与人造卫星信号进行方位角测量的天线姿态传感器 | CN201620567255.0 | 2016-06-12 | CN205825970U | 2016-12-21 | 张志军; 曹晓京 |
| 一种利用和差波束天线与人造卫星信号进行方位角测量的天线姿态传感器，在基站天线位置设置用于产生和波束及差波束两种形式波束的和差波束天线作为接收天线，对人造卫星的信号同时或先后进行接收，比较不同波束的输出信号强度变化，在差波束的输出信号强度与和波束的输出信号强度的差别达到最大时，差波束的接收凹点所面对的方向就是卫星的方位角，即天线的方位角；本实用新型利用和差波束天线与人造卫星信号测量方位角，利用陀螺仪持续跟踪测量天线方位角变化，利用三轴重力加速度传感器测量天线俯仰角，并利用蓄电池和外接电源为传感器供电，可精确测量基站天线姿态，结构简单，成本低，便于生产。 | ||||||
| 90 | 인공위성을 이용한 에이디에스엘 서비스 장치 | KR1020010020230 | 2001-04-16 | KR1020020080589A | 2002-10-26 | 이기영; 박성호; 주광진 |
| PURPOSE: An ADSL(Asymmetric Digital Subscriber Line) service device using an artificial satellite is provided to transmit data through a telephone line and to receive data through the artificial satellite, so that an upload speed as well as a download speed is raised. CONSTITUTION: In a subscriber device(900), a satellite receiving unit(200) receives signals of a predetermined downstream channel from a satellite(400). A filtering unit(150) filters signals in a frequency band of the downstream channel and filters signals in a frequency band of an upstream channel through a telephone line. A modem(110) demodulates the filtered downstream channel signals and modulates the upstream channel signals. The subscriber device(900) transmits upstream channel data to a telephone office(700) through the filtering unit(150). The telephone office(700) transmits downstream channel data to be transmitted to a subscriber to a satellite data station(600). The satellite data station(600) transmits the received downstream channel signals to a satellite transmission antenna(500). The downstream channel signals passes through the satellite(400) and are received to a satellite receiving antenna(300), thus being inputted to the satellite receiving unit(200). | ||||||
| 91 | 인공위성을 이용한 인터넷 서비스 시스템 | KR1020000045068 | 2000-08-03 | KR1020020011653A | 2002-02-09 | 지환국 |
| PURPOSE: An Internet service system using an artificial satellite is provided to connect various subscriber networks with television systems using a set-top box so as to enable both way communication, to allow users to be able to be provided with ultra-high-speed artificial satellite Internet service without purchasing computer systems. CONSTITUTION: An Internet service system using an artificial satellite has a main server(10) providing information services including shopping information, chatting service, mail service and network games and a variety of Internet services according to a user's choice, and a relay server(20) that is connected with a plurality of users(60) through a subscriber network(40), transmits an information request signal of each user to the main server and sends information data delivered from the main server to each user through the subscriber networks. The system further includes a satellite transmitter/receiver(31,32) that is connected to each of the main server and the relay server and transmits/receives a data information signal between the main server and the relay server using both way communication through an artificial satellite, and a set-top box(50) connected between the subscriber network and the users to enable both way communication. | ||||||
| 92 | 인공위성을 이용한 인터넷 서비스 시스템 | KR1020000021008 | 2000-04-20 | KR1020010097171A | 2001-11-08 | 지환국 |
| 사용자가 낮은 비용 부담으로 초고속의 위성 인터넷 서비스를 제공받을 수 있도록 하기 위하여, 사용자 선택에 따른 쇼핑 정보, 채팅 서비스, 메일 서비스, 네트웍 게임을 포함한 정보 서비스 및 다양한 인터넷 서비스를 제공하여 주는 메인 서버와, 다수의 사용자를 네트웍으로 연결하여 주며, 각 사용자들의 정보 요구 신호를 상기 메인 서버로 전송하여 주고, 상기 메인 서버로부터 전송되는 정보 데이터를 각 사용자측으로 전송하여 주는 중계 서버와, 상기 메인 서버와 중계 서버에 각각 접속되며, 상기 메인 서버와 중계 서버 사이의 데이터 정보 신호를 인공위성을 통한 양방향 통신으로 송수신하여 주는 위성 송수신기를 포함하여 중계 서버를 통해 다수의 사용자들을 네트웍으로 접속하도록 하고, 중계 서버와 다양한 인터넷 서비스를 제공하는 메� �� 서버 사이의 통신을 인공위성을 통해 이루어지도록 함으로써 사용자는 위성 인터넷 서비스 이용을 위한 수신기 등의 장비를 설치하지 않고도 낮은 비용 부담으로 초고속의 위성 인터넷 서비스를 이용할 수 있게 된다. | ||||||
| 93 | 인공위성용배터리감시장치 | KR1019980047236 | 1998-11-05 | KR1020000031282A | 2000-06-05 | 이상곤 |
| PURPOSE: A device for monitoring a battery is provided to automatically keep a battery without monitoring an additional worker by automatically blocking a charging current until the charging current is re-injected by removing a cause of generation of abnormality. CONSTITUTION: A battery(11) is kept inside a chamber(10), and a charging current is supplied through a relay(43). Herein, a temperature sensor for sensing a temperature inside the battery and the chamber and a voltage and a current sensor for sensing the charging voltage and current of the battery are installed in the chamber. A sending voltage of the sensor of a temperature, a voltage and a current is detected in a sensing IC(20), and a computer(30) sets up the ranges of the temperature, voltage, and current by using a general personal computer. In addition, the range of monitor of the computer set up by a user is compared with a sensor output in the sensing IC(20). That is, if the sensing output is not in the range of monitor set up in the computer, the sensing IC outputs an alarm signal. | ||||||
| 94 | 인공위성의자세전환실험장치 | KR1019930026761 | 1993-12-07 | KR1019970005470B1 | 1997-04-16 | 강자영; 신광근; 김재한 |
| The position change test device of an artificial satellite comprises: a satellite body drum(1) having a rotating shaft(1) on the center of the upper and lower surfaces thereof; a driven gear(2) for rotating the drum(1); a position change means installed on a predetermined position of the drum(1); an internal square member(9); an external square member(11); a main supporting means for freely rotating the internal and external square members(9,11); driving means(17,18); a rotating means(15); at least one or more sensing means(8) for sensing a target position to be directed by the satellite body; a driven disc gear(13); and brake and position control means(19,20) for receiving the sensed information of the sensing means. | ||||||
| 95 | 人造衛星天線 | TW077305887 | 1988-10-11 | TW119026S | 1989-09-11 | 派崔克.坎貝爾.亨特 |
| 96 | 人造卫星模型 | CN202130829062.4 | 2021-12-15 | CN307245567S | 2022-04-08 | 俞放; 李宗琛 |
| 1.本外观设计产品的名称：人造卫星模型。 2.本外观设计产品的用途：展示卫星结构和工作状态。 3.本外观设计产品的设计要点：在于形状。 4.最能表明设计要点的图片或照片：组合状态立体图。 | ||||||
| 97 | 태양전지판 전개모듈 및 이를 포함하는 인공위성 | KR1020120036704 | 2012-04-09 | KR101442506B1 | 2014-09-23 | 이민규; 홍주성 |
| 태양전지판 전개모듈 및 이를 포함하는 인공위성이 개시된다.
본 발명의 일 실시예에 따른 태양전지판은, 인공위성의 몸체와 연결되며, 길이 방향으로 길게 형성된 중심부재를 포함하며, 양단부에는 각각 제1전지판이 각도 조절 가능하게 연결되는 메인프레임, 상기 메인프레임의 양단부 사이에 위치되는 이동부재, 상기 이동부재에 구비되며, 외력에 의해 파단되어 상기 이동부재를 제1파트 및 제2파트로 분할하는 파단부, 상기 제1전지판과 상기 이동부재를 각각 연결하는 연결링크 및 인장된 상태로 상기 이동부재의 양측과 상기 메인프레임의 양단부를 각각 연결하며, 상기 타단부가 파단 시 상기 제1파트 및 상기 제2파트를 상기 메인프레임의 양단부 측으로 각각 이동시키는 인장탄성부재를 포함한다. 그리고 본 발명의 다른 실시예에 따른 태양전지판은, 인공위성의 몸체와 연결되며, 길이 방향으로 길게 형성된 중심전지판을 포함하며, 일단부에는 제1전지판이 각도 조절 가능하게 연결되는 제2전지판, 상기 제2전지판의 일단부로부터 이격되어 위치되며, 적어도 일부가 상기 제2전지판에 고정되는 이동부재, 상기 이동부재에 구비되며, 외력에 의해 파단되어 상기 이동부재의 고정 상태를 해제하는 파단부, 상기 태양전지판과 상기 이동부재를 연결하는 연결링크 및 인장된 상태로 상기 이동부재와 상기 제2전지판의 일단부를 각각 연결하며, 상기 타단부가 파단 시 상기 이동부재를 상기 제2전지판의 일단부 측으로 이동시키는 인장탄성부재를 포함한다. |
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| 98 | 인공위성용 광학 렌즈의 초정밀 위치 정렬 장치 | KR1020090122622 | 2009-12-10 | KR101082755B1 | 2011-11-10 | 이동우; 문상무; 임종민; 은희광; 문남진 |
| 본발명은인공위성용광학렌즈의초정밀위치정렬장치에관한것으로, 보다상세하게는인공위성에사용되는광학렌즈의위치를 5축방향으로정밀하게정렬하여상기광학렌즈의위치를제어하기위한인공위성용광학렌즈의초정밀위치정렬장치에관한것이다. 본발명에따른인공위성용광학렌즈의초정밀위치정렬장치에의하면, X축방향으로각각이동하는제 1 X축스테이지및 제 2 X축스테이지와 Y축방향으로각각이동하는제 1 Y축스테이지및 제 2 Y축스테이지의위치정렬에의하여 X축, Y축및, Z축의 3축방향의병진운동(translation) 뿐만아니라 X축중심의회전운동(elevation)과 Y축중심의회전운동(azimuth)에대하여미세하고정밀한위치정렬을제어할수 있는현저한효과가있다. | ||||||
| 99 | 태양전지판 전개장치 및 이를 포함하는 인공위성 | KR1020080070614 | 2008-07-21 | KR1020100009812A | 2010-01-29 | 김경원; 김선원; 임재혁; 이주훈; 황도순; 송운형; 최항석; 김진희; 진익민; 김학정 |
| PURPOSE: A solar cell panel unfolding device and an artificial satellite having the same are provided to improve the rigidity of the solar cell panel unfolding device by unfolding the solar panel in the artificial satellite main body. CONSTITUTION: A hinge unit connects the artificial satellite main body and a solar panel. A first unfolding unit(120) has two hinge brackets(121,124) which are mutually corresponded shape. The first unfolding unit is connected to the artificial satellite main body. A second unfolding unit(140) has third and fourth hinge brackets(141,144). The second unfolding unit is connected to the solar panel. A connecting unit(160) folds or unfolds the first and second unfolding units. | ||||||
| 100 | 인공 위성의 제어 신호 검증 장치 및 방법 | KR1020070125229 | 2007-12-05 | KR1020090058606A | 2009-06-10 | 박병하; 최종연; 권재욱; 윤영수; 조승원; 김영윤 |
| An artificial satellite control signal verification apparatus and a method are provided to verify an electromagnetic filed signal and a valve control signal selectively by assembling a control signal verify device of an artificial satellite and the artificial satellite. An interface unit(520) supplies power to an artificial satellite from a power supply unit(510), and receives more than an electromagnetic filed signal and a valve signal from the artificial satellite body. A verification unit(530) processes more than one of the received electromagnetic filed signal and a valve signal, and verifies whether a normal condition of a posture control system or not through the received valve signal, and it also verify whether a normal condition of a solar panel through the received electromagnetic filed. | ||||||
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