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公开(公告)号：KR1020170048087A
公开(公告)日：2017-05-08
申请号：KR1020150149001
申请日：2015-10-26
Applicant: 한국항공우주연구원
CPC classification number: G08G5/025 , G01S19/15 , G05D1/0676 , G08G5/0021
Abstract: 본발명은, 항공기착륙을위한착륙수신장치및 그제어방법에관한것으로, 본발명에따른착륙수신장치는사용자로부터착륙예정공항, 착륙예정활주로및 수신기모드를입력받는 FMS, 항공기의착륙을위한최종접근경로데이터를저장하는데이터저장부, 입력된수신기모드가 GNSS/SBAS 통합모드인경우, 안테나부로부터전송된 GNSS 신호와 SBAS 신호를이용하여항공기위치정보를계산하는수신기부, 그리고입력된착륙예정공항및 착륙예정활주로에대응하는최종접근경로데이터와항공기위치정보를이용하여착륙유도정보를생성하고, 생성된착륙유도정보를 FMS에전달하는착륙유도정보생성부를포함한다.
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Patent Agency Ranking
公开(公告)号：KR101392068B1
公开(公告)日：2014-05-07
申请号：KR1020120082350
申请日：2012-07-27
Applicant: 건국대학교 산학협력단 , 한국항공우주연구원
Abstract: 기저선정보를이용한위성항법시스템의고장검출장치및 그방법이개시된다. 본발명의일실시예에따른기저선정보를이용한위성항법시스템의고장검출장치및 그방법은위성으로부터수신된항법메시지로부터위성좌표를계산하는위성좌표계산부; 상기위성과제1 수신기간의위성거리를측정하는위성거리측정부; 상기제1 수신기와인접한제2 수신기간의기저선벡터와상기계산된위성좌표를이용하여상기위성및 상기제2 수신기간의제2 위성벡터를계산하고, 상기계산된기저선벡터와제2 위성벡터를이용하여상기위성과제1 수신기간의제1 위성벡터를계산하는벡터계산부; 및상기계산된제1 위성벡터의크기와상기측정된위성과제1 수신기간의위성거리측정값을비교하여위성항법시스템의고장을검출하는고장검출부를포함한다.
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公开(公告)号：KR101827820B1
公开(公告)日：2018-02-09
申请号：KR1020150149001
申请日：2015-10-26
Applicant: 한국항공우주연구원
CPC classification number: G08G5/025 , G01S19/15 , G05D1/0676 , G08G5/0021
Abstract: 본발명은, 항공기착륙을위한착륙수신장치및 그제어방법에관한것으로, 본발명에따른착륙수신장치는사용자로부터착륙예정공항, 착륙예정활주로및 수신기모드를입력받는 FMS, 항공기의착륙을위한최종접근경로데이터를저장하는데이터저장부, 입력된수신기모드가 GNSS/SBAS 통합모드인경우, 안테나부로부터전송된 GNSS 신호와 SBAS 신호를이용하여항공기위치정보를계산하는수신기부, 그리고입력된착륙예정공항및 착륙예정활주로에대응하는최종접근경로데이터와항공기위치정보를이용하여착륙유도정보를생성하고, 생성된착륙유도정보를 FMS에전달하는착륙유도정보생성부를포함한다.
Abstract translation: 本发明涉及一种着陆接收装置和用于飞机着陆的控制方法，根据本发明着陆接收机，最终着陆将机场，着陆的着陆将FMS，飞机从用户接收跑道和接收器模式 接收单元，用于当输入接收器模式是GNSS / SBAS集成模式时，使用从天线单元发送的GNSS信号和SBAS信号来计算飞行器的位置信息， 机场以及使用所述最后进近路径数据和对应于所调度的着陆跑道着陆飞机位置信息生成导出的信息，并且包括产生提供所产生的信息到着陆感应FMS着陆导出的信息。
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公开(公告)号：KR1020140014945A
公开(公告)日：2014-02-06
申请号：KR1020120082350
申请日：2012-07-27
Applicant: 건국대학교 산학협력단 , 한국항공우주연구원
Abstract: Disclosed are an apparatus for detecting a fault of a global navigation satellite system using baseline information and a method thereof. The apparatus for detecting a fault of a global navigation satellite system using baseline information and the method thereof according to an embodiment of the present invention includes: a satellite coordinate calculation unit for calculating satellite coordinates from a navigation message received from a satellite; a satellite distance measurement unit for measuring satellite distance between the satellite and a first receiver; a vector calculation unit for calculating a second satellite vector between the satellite and a second receiver using the calculated satellite coordinates and a baseline vector between the first receiver and an adjacent second receiver, and for calculating a first satellite vector between the satellite and the first receiver using the calculated baseline vector and the second satellite vector; and a fault detection unit for detecting a fault of the global navigation satellite system by comparing the amplitude of the calculated first satellite vector with the measured satellite distance measurement value between the satellite and the first receiver. [Reference numerals] (100) Fault detection apparatus of global navigation satellite system; (110) Satellite coordinate calculation unit; (120) Satellite distance measurement unit; (130) Vector calculation unit; (140) Fault detection unit
Abstract translation: 公开了一种使用基线信息检测全球导航卫星系统的故障的装置及其方法。 根据本发明实施例的使用基线信息检测全球导航卫星系统故障的装置及其方法包括：卫星坐标计算单元，用于从卫星接收的导航信息中计算卫星坐标; 卫星距离测量单元，用于测量卫星与第一接收机之间的卫星距离; 矢量计算单元，用于使用所计算的卫星坐标和第一接收机与相邻的第二接收机之间的基线矢量来计算卫星和第二接收机之间的第二卫星矢量，并且用于计算卫星和第一接收机之间的第一卫星矢量 使用计算的基线矢量和第二卫星矢量; 以及故障检测单元，用于通过将所计算的第一卫星矢量的幅度与卫星和第一接收机之间的测量的卫星距离测量值进行比较来检测全球导航卫星系统的故障。 （附图标记）（100）全球导航卫星系统故障检测装置; （110）卫星坐标计算单元; （120）卫星测距单位; （130）向量计算单元; （140）故障检测单元
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5.发明授权
公开(公告)号：KR101363226B1
公开(公告)日：2014-02-14
申请号：KR1020120122861
申请日：2012-11-01
Applicant: 건국대학교 산학협력단 , 한국항공우주연구원
Abstract: The present invention relates to a method for deploying a base station antenna to improve fault detection of a global navigation satellite message and a fault detection apparatus of the global navigation satellite message. The method for deploying a base station antenna to improve fault detection of a global navigation satellite message received from a satellite of the present invention includes: an apex coordinate calculation step of calculating each apex coordinate of a polygon corresponding to the number of a plurality of base station antennas; and an antenna deployment step of deploying each of the plurality of base station antennas at each calculated apex coordinate of the polygon in order to generate a base line among the plurality of base station antennas, by moving one base station antenna among the plurality of deployed base station antennas to generate an additional base line which is independent of the generated base line. [Reference numerals] (121) Receiver A; (122) Receiver B; (123) Receiver C; (124) Receiver D
Abstract translation: 本发明涉及一种用于部署基站天线以改善全球导航卫星消息的故障检测和全球导航卫星消息的故障检测装置的方法。 用于部署基站天线以改善从本发明的卫星接收的全球导航卫星消息的故障检测的方法包括：顶点坐标计算步骤，计算与多个基站的数量对应的多边形的每个顶点坐标 站天线; 以及天线部署步骤，通过在多个基站天线之间移动一个基站天线，将多个基站天线中的每一个部署在多边形的每个计算出的顶点坐标处，以便生成多个基站天线之间的基准线 以产生独立于所生成的基线的附加基线。 （附图标记）（121）接收器A; （122）接收器B; （123）接收者C; （124）接收者D
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公开(公告)号：KR101223308B1
公开(公告)日：2013-01-16
申请号：KR1020110094870
申请日：2011-09-20
Applicant: 건국대학교 산학협력단 , 한국항공우주연구원
Abstract: PURPOSE: A failure detecting system for a receiver of a satellite navigation system for transportation means is provided to detect a satellite navigation receiving failure of transportation means based on multiple satellite navigations easily, and secure the integrity of satellite navigation receiving. CONSTITUTION: A failure detecting system for a receiver of a satellite navigation system for transportation means comprises the following steps: A satellite navigation receiving apparatus of a reference station(200) comprises a receiving unit(210), a distance calculating unit(220), a correction data generating unit(230), and a transmitting unit(240). The receiving unit receives satellite navigation data from the satellite, correction data from the receiving apparatuses of the reference station, and multiple correction data from the receiving apparatuses of multiple peripheral transportation means. The distance calculating unit calculates the position of transportation means by using the received satellite navigation data and the correction data. The correction data generating unit produces the correction data by using the received satellite navigation data generated according to the calculated position of the transportation means. The transmitting unit transmits the correction data to the receiving apparatuses of the multiple peripheral transportation means. [Reference numerals] (210) Receiving unit; (220) Distance calculating unit; (230) Correction data generating unit; (240) Transmitting unit
Abstract translation: 目的：提供一种用于运输工具的卫星导航系统的接收机的故障检测系统，用于轻松地基于多个卫星导航来检测运输工具的卫星导航接收故障，并确保卫星导航接收的完整性。 构成：用于运输工具的卫星导航系统的接收机的故障检测系统包括以下步骤：参考站（200）的卫星导航接收装置包括接收单元（210），距离计算单元（220） 校正数据生成单元（230）和发送单元（240）。 接收单元从卫星接收卫星导航数据，来自参考站的接收装置的校正数据和来自多个外围传送装置的接收装置的多个校正数据。 距离计算单元通过使用接收到的卫星导航数据和校正数据来计算运送装置的位置。 校正数据生成单元通过使用根据计算出的运送单元的位置生成的接收到的卫星导航数据来生成校正数据。 发送单元将校正数据发送到多个周边运送装置的接收装置。 （附图标记）（210）接收单元; （220）距离计算单位; （230）校正数据生成单元; （240）发送单元
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