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公开(公告)号：KR1020140124889A
公开(公告)日：2014-10-28
申请号：KR1020120042481
申请日：2012-04-24
Applicant: 국방과학연구소
IPC: G01N21/954 , G01B11/16 , F41A31/00
Abstract: The present invention relates to a device for measuring the corrosion of a bore using a vision system capable of quickly, accurately, and automatically measuring the internal crack state and corroded position and the depth of a bore by using a focused light generation part for displaying the corroded depth and a CCD image sensor. The device comprises: a measurement device body (100) linearly moving in the bore (410) of a gun barrel (400), and measuring the internal crack state and corroded position and the depth of the bore (410) using the focused light generation part (120) for displaying the corroded depth by irradiating focused light and a color CCD image sensor assembly (150); and a control device (200) for processing and revealing all kinds of data transmitted from the measurement device body (100), and for remote-controlling the measurement device body (100).
Abstract translation: 本发明涉及一种使用视觉系统测量孔的腐蚀的装置，该视觉系统能够通过使用聚焦光产生部件来快速，准确和自动地测量内部裂纹状态和腐蚀位置以及孔的深度， 腐蚀深度和CCD图像传感器。 该装置包括：测量装置主体（100），其在枪筒（400）的孔（410）中线性运动，并且使用聚焦光产生来测量内部裂纹状态和腐蚀位置以及孔（410）的深度 用于通过照射聚焦光来显示腐蚀深度的部分（120）和彩色CCD图像传感器组件（150）; 以及用于处理和显示从测量装置主体（100）发送的各种数据的控制装置（200），并且用于远程控制测量装置主体（100）。
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公开(公告)号：KR101426289B1
公开(公告)日：2014-08-05
申请号：KR1020130002578
申请日：2013-01-09
Applicant: 국방과학연구소
Abstract: 본 명세서는 항공기 계기 비행에 측면 항법을 적용하는 기동 헬기 측면 항법 운용 장치 및 그 방법에 관한 것이다. 이를 위하여 본 명세서에 따른 기동 헬기 측면 항법 운용 장치는, 제1 및 제2 자동 조종 컴퓨터, 데이터 획득 처리 장치 및, 초단파 전방향 거리탐지기와 연동하는 이중 구조로 형성되는 기동 헬기 측면 항법 운용 장치에 있어서, 상기 기동 헬기 측면 항법 운용 장치는, 주요 비행정보 시현 페이지를 표시하며, 상기 표시 중인 주요 비행정보 시현 페이지에서 선택된 항법 소스의 모드를 확인하는 제1, 제2, 제3 및, 제4 다기능시현기; 상기 기동 헬기 측면 항법 구동을 위한 하나 이상의 파라미터 값을 설정하는 제1 및 제2 통제시현장치; 항로 노브를 설정하는 제1 및 제2 비행조종 패널; 및 상기 선택된 항법 소스 모드가 비행 계획, 초단파 전방향 거리탐지기/계기착륙장치, 홈 모드일 때, 상기 제1 및 제2 비행조종 패널의 항로 노브로 설정된 수동 항로 방향을 근거로 계획된 구간을 설정하고, 롤 명령을 계산하는 제1 및 제2 임무 컴퓨터;를 포함한다.
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公开(公告)号：KR101538321B1
公开(公告)日：2015-07-22
申请号：KR1020140157387
申请日：2014-11-12
Applicant: 국방과학연구소
CPC classification number: H04L12/2834 , H04L1/0004 , H04L41/0836
Abstract: 본발명은수중배열센서의신호전송노드에고장이발생한경우데이터손실을최소화하기위한데이터전송시스템을제공한다. 이를위하여상기신호전송노드에신호전송부, 디지털회로, 아날로그회로및 전원공급부를포함하고, 상기디지털회로에는주 제어부, 스위치및 부제어부를포함한다. 상기디지털회로의제어부를분리함으로써, 상기주 제어부에고장이발생하여도상기부 제어부가수신된데이터의전송경로를제어하여전송하기때문에고장으로인한데이터손실이방지된다. 또한, 데이터손실의감소로수중배열센서의탐지성능이향상되는효과가있다.
Abstract translation: 提供了如果发生水下阵列传感器的信号传送节点的故障，则最小化数据丢失的数据传输系统。 信号传送节点包括：信号传送部分; 数字电路; 一个模拟电路; 和电源部。 数字电路包括：主控制部分; 开关 和子控制部分。 通过分离数字电路的控制部分，防止由故障引起的数据丢失，因为如果在主控制部分发生故障，则子控制部分控制并传送接收数据的传送路径。 此外，由于数据丢失的减少，水下阵列传感器的检测性能得到改善。
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公开(公告)号：KR1020140090477A
公开(公告)日：2014-07-17
申请号：KR1020130002578
申请日：2013-01-09
Applicant: 국방과학연구소
CPC classification number: G01C21/20
Abstract: The present specification relates to an apparatus and a method for operating lateral navigation in a utility helicopter in which the lateral navigation is applied to aeronautical instrument flying. The apparatus for operating the lateral navigation in the utility helicopter according to the present specification comprises a first, a second, a third, and a fourth multifunctional display for displaying a main flying information display page and for confirming a mode of a navigation source selected in the displayed main flying information display page; a first and a second control apparatus for setting one or more parameter values for operating the lateral navigation in the utility helicopter; a first and a second flying control panel for setting a course knob; and a first and a second assignment computer for setting a section planned based on a manual course direction set by the course knob of the first and the second flying control panel and for calculating a role command when the selected navigation source mode is a flying plan, very high frequency front direction distance detector/instrument landing apparatus, and a home mode in the apparatus for operating the lateral navigation in the utility helicopter having a dual structure connected to a first and a second automatic control computer, a data processor, and the very high frequency front direction distance detector.
Abstract translation: 本说明书涉及一种用于在实用直升机中操作侧向导航的装置和方法，其中侧向导航应用于航空飞行。 根据本说明书的用于在实用直升机中操作侧向导航的装置包括第一，第二，第三和第四多功能显示器，用于显示主飞行信息显示页面并且用于确认在主飞行信息显示页面中选择的导航源的模式 显示主飞行信息显示页面; 第一和第二控制装置，用于设置用于在实用直升机中操作侧向导航的一个或多个参数值; 第一和第二飞行控制面板，用于设置踏板旋钮; 以及第一和第二分配计算机，用于根据由第一和第二飞行控制面板的航向旋钮设置的手动航向方向来设定计划的部分，并且当所选择的导航源模式是飞行计划时计算角色命令， 超高频前方距离检测器/仪器着陆装置，以及用于操作实用直升机中的侧向导航的装置中的家庭模式，其具有连接到第一和第二自动控制计算机，数据处理器和非常 高频前方距离探测器。
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公开(公告)号：KR1020120027869A
公开(公告)日：2012-03-22
申请号：KR1020100089679
申请日：2010-09-13
Applicant: 국방과학연구소
Abstract: PURPOSE: An active sonar system and an impedance matching method are provided to improve output performance and detection performance. CONSTITUTION: A transmission part of an active sonar system(100) comprises a transmitter(110), a transducer(120), and an impedance matching circuit(130). The transmitter is modeled with input power and input impedance. The transducer converts an electric signal of the transmitter into a sound wave or vice versa. The impedance matching circuit transmits the energy of the transmitter to the transducer with high efficiency.
Abstract translation: 目的：提供主动声纳系统和阻抗匹配方法，以提高输出性能和检测性能。 构成：主动声纳系统（100）的传输部分包括发射器（110），换能器（120）和阻抗匹配电路（130）。 变送器用输入功率和输入阻抗建模。 换能器将发射机的电信号转换成声波，反之亦然。 阻抗匹配电路以高效率将发射机的能量传输到换能器。
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Patent Agency Ranking
公开(公告)号：KR101096521B1
公开(公告)日：2011-12-20
申请号：KR1020100089680
申请日：2010-09-13
Applicant: 국방과학연구소
Abstract: PURPOSE: A method for the estimating equivalent model parameter of a transducer and a sonar system using the same are provided to accurately execute modeling by considering an interference effect between resonance modes in an acoustic wave band and a supersonic wave band. CONSTITUTION: A sonar system comprises a transmitter(110), an impedance matching circuit(230), and a transducer(220). The transmitter is modeled to input power source and input impedance. The transducer changes an electric signal of the transmitter into a sound wave or changes an external electric signal into the electric signal. The impedance matching circuit transmits a power amount between transmitters to the transducer. The transducer estimates individual mode impedance and entire mode impedance from multiplex mode impedance data. The transducer is modeled an electrical equivalent model having a plurality of shifts corresponding to each mode by considering the interference amount of an adjacency mode.
Abstract translation: 目的：提供一种用于估计换能器和使用其的声纳系统的等效模型参数的方法，以通过考虑声波波段和超声波波段中的谐振模式之间的干扰效应来精确地执行建模。 构成：声纳系统包括发射器（110），阻抗匹配电路（230）和换能器（220）。 变送器被建模为输入电源和输入阻抗。 换能器将发射器的电信号改变成声波或将外部电信号改变为电信号。 阻抗匹配电路将发射器之间的功率量传输到换能器。 传感器从多路复用模式阻抗数据估计单模阻抗和整模阻抗。 通过考虑邻接模式的干扰量，将换能器建模为具有对应于每个模式的多个位移的电等效模型。
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公开(公告)号：KR1020140090478A
公开(公告)日：2014-07-17
申请号：KR1020130002579
申请日：2013-01-09
Applicant: 국방과학연구소
Abstract: The present specification relates to an integrated survivability demonstration apparatus of an aircraft which integrates a radar warning receiver, a laser warning receiver, a missile warning receiver, and a chaff/flare dispenser into an avionic system; and a method thereof. According to the present invention, the integrated survivability demonstration apparatus of the aircraft includes: an electronic warfare computer interlocked with a radar warning receiver, a laser warning receiver, a missile warning receiver, and a chaff/flare dispenser. The integrated survivability demonstration apparatus of the aircraft comprises: a plurality of mission computers receiving threat information, state information and response result information; a plurality of multifunctional demonstrators demonstrating the received treat information, state information and response result information by controlling the mission computers; and a plurality of control demonstrators demonstrating a plurality of components.
Abstract translation: 本说明书涉及将航空电子系统中的雷达警报接收器，激光警报接收器，导弹警告接收器和谷壳/火炬分配器集成的飞行器的综合生存性演示装置; 及其方法。 根据本发明，飞行器的综合生存演示装置包括：与雷达警报接收器，激光警告接收器，导弹警告接收器和谷壳/火炬分配器联锁的电子战计算机。 飞机的综合生存能力演示装置包括：多个任务计算机接收威胁信息，状态信息和响应结果信息; 多个多功能示威者，通过控制任务计算机来演示收到的待处理信息，状态信息和响应结果信息; 以及展示多个部件的多个控制演示器。
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公开(公告)号：KR101649510B1
公开(公告)日：2016-08-22
申请号：KR1020130002579
申请日：2013-01-09
Applicant: 국방과학연구소
Abstract: 본명세서는레이더경보수신기, 레이저경보수신기, 미사일경보수신기및, 채프/플레어발사기등의각각의시현장치를항공전자장치에통합시키는항공기용통합형생존시현장치및 그방법에관한것이다. 이를위하여본 명세서에따른항공기용통합형생존시현장치는, 레이더경보수신기, 레이저경보수신기, 미사일경보수신기및, 채프/플레어발사기와연동하는생존장비관리컴퓨터를포함하는항공기용통합형생존시현장치에있어서, 상기항공기용통합형생존시현장치는, 상기생존장비관리컴퓨터로부터전달되는위협정보, 상태정보및, 대응결과정보를수신하는복수의임무컴퓨터; 상기복수의임무컴퓨터의제어에의해, 상기수신된위협정보, 상태정보및, 대응결과정보를시현하는복수의다기능시현기; 및복수의구성품을시현하는복수의통제시현장치;를포함한다.
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公开(公告)号：KR101480863B1
公开(公告)日：2015-01-13
申请号：KR1020120042481
申请日：2012-04-24
Applicant: 국방과학연구소
IPC: G01N21/954 , G01B11/16 , F41A31/00
Abstract: 본 발명은 마모 깊이를 표시하는 집속광 발생부와 CCD 이미지 센서를 이용하여 신속 정확하게 포강 내부의 균열 상태와 마모 위치 및 그 깊이를 자동으로 측정할 수 있도록 한 비젼 시스템을 이용한 포강마모 측정장치에 관한 것으로서,
포신(400)의 포강(410) 내부에서 직선 이동하며, 포강 표면으로 집속광을 조사하여 마모 깊이를 표시하는 집속광 발생부(120)와 컬러 CCD 이미지 센서 조립체(150)를 이용하여 포강(410) 내면의 균열 상태와 마모 위치 및 깊이를 측정하는 측정장치 본체(100)와; 상기 측정장치 본체(100)로부터 전송된 각종 데이터를 처리 및 시현하고 상기 측정장치 본체(100)를 원격 조정 및 통제하는 제어장치(200);를 포함하는 것을 특징으로 한다.-
公开(公告)号：KR1020140090867A
公开(公告)日：2014-07-18
申请号：KR1020130003039
申请日：2013-01-10
Applicant: 국방과학연구소
CPC classification number: B64D43/00 , G01C21/20 , G01C23/005
Abstract: The present specification relates to an apparatus for driving required navigation performance of a mobile helicopter and a method thereof for implementing the required navigation performance by flight phase. The apparatus for driving required navigation performance of a mobile helicopter according to the present specification comprises a plurality of multi-functional demonstration devices for displaying a main flight information demonstration page and checking a selected navigation source mode from the main flight information demonstration page in display; a plurality of demonstration control devices for setting one or more parameter values for driving the required navigation performance of the mobile helicopter; and a plurality of mission computers for demonstrating required navigation flight phases on the flight information demonstration page of the multi-functional demonstration devices when the selected navigation source mode is a flight planning and a home mode, and automatically changing a fly-by waypoint and a fly-over waypoint based on required navigation performance conditions by flight phase corresponding to the selected required performance flight phase menu when one is selected from the required performance flight phase menus included in the demonstrated required navigation performance flight phase.
Abstract translation: 本说明书涉及一种用于驾驶移动直升机所需导航性能的装置及其方法，用于通过飞行阶段来实现所需导航性能。 根据本说明书的移动式直升机驾驶所需的导航性能的装置包括多个多功能演示装置，用于显示主飞行信息演示页面，并从显示的主飞行信息演示页面检查所选择的导航源模式; 多个演示控制装置，用于设定用于驱动移动直升机所需导航性能的一个或多个参数值; 以及多个任务计算机，用于在所选择的导航源模式是飞行计划和归属模式时，在多功能演示装置的飞行信息演示页面上演示所需的导航飞行阶段，并且自动地改变飞行路线点和 根据所需的导航性能条件，飞行阶段对应于所选择的所需性能飞行阶段菜单，当从所需的性能飞行阶段菜单中选择包括在演示的所需导航性能飞行阶段时，飞行航路点。
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