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公开(公告)号：KR1020130041696A
公开(公告)日：2013-04-25
申请号：KR1020110106126
申请日：2011-10-17
Applicant: 국방과학연구소
CPC classification number: G09B9/003 , G06F9/45504
Abstract: PURPOSE: A device for developing a portable avionics system and an operation method thereof are provided to be implemented by software operated on a general purpose operating system and to be manufactured at low costs. CONSTITUTION: A simulation unit(12) executes a simulation model corresponding to avionics equipment and performs simulation. A display unit displays a simulation performance result. A storage unit stores a simulation model, a simulation engine, and a general purpose operating system. A control unit performs simulation for the avionics equipment. [Reference numerals] (11) Operator interface unit; (12) Simulation unit; (13) Aviation electronics equipment unit;
Abstract translation: 目的：开发便携式航空电子系统的装置及其操作方法由通用操作系统上运行的软件实现，并以低成本制造。 构成：仿真单元（12）执行与航空电子设备相对应的仿真模型，进行仿真。 显示单元显示模拟性能结果。 存储单元存储模拟模型，模拟引擎和通用操作系统。 控制单元对航空电子设备进行仿真。 （附图标记）（11）操作者界面单元; （12）模拟单元; （13）航空电子设备单位;
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2.发明授权항공기의 비행 필수 시현 시스템, 항공기의 비행 필수 시현 시스템의 센서 고장 분리 방법 및 항공기 고도 비행경고 시현 방법 有权飞行器飞行监测装置，传感器故障分离方法和航行报警监测方法
公开(公告)号：KR101212218B1
公开(公告)日：2012-12-13
申请号：KR1020110101506
申请日：2011-10-05
Applicant: 국방과학연구소
CPC classification number: B64D43/00 , B64D43/02 , G01C23/005
Abstract: PURPOSE: A flight simulation system for an aircraft, a method for separating a malfunctioned sensor thereof, and an altitude flight alarm simulation method for the aircraft can efficiently provide vital flight data on the flight and navigation of an aircraft to a pilot. CONSTITUTION: A flight simulation system for an aircraft comprises a first sensor device(131), a second sensor device(132), a first automatic flight device, a second automatic flight device, first task computer(121), a second task computer(122), a fist simulation part, a second simulation part, an independent gauge, and a selection switch. When one of the first and second sensor devices is normally operated, the other one is operated in a backup mode. The first and second automatic flight devices make an aircraft automatically fly based on signals detected from the first or second sensor device. The first and second task computers control one of the first and second automatic flight devices with the signals detected from the first or second sensor device. The first simulation part simulates information on the first sensor device and the first automatic flight device. The second simulation part simulates information on the second sensor device and a second automatic flight device. The independent gauge displays flight information which is independent to the first and second sensor devices. The selection switch is operated to ignore the signals transmitted from one of the sensor devices exceeding a predetermined threshold valve.
Abstract translation: 目的：飞机的飞行模拟系统，分离其故障传感器的方法和飞机的高空飞行警报模拟方法可以有效地为飞行员的飞行和导航飞行提供重要的飞行数据。 构成：飞行器的飞行模拟系统包括第一传感器装置（131），第二传感器装置（132），第一自动飞行装置，第二自动飞行装置，第一任务计算机（121），第二任务计算机 122），第一模拟部分，第二模拟部分，独立量规和选择开关。 当第一和第二传感器装置中的一个正常操作时，另一个传感器装置在备用模式下操作。 第一和第二自动飞行装置使得飞行器基于从第一或第二传感器装置检测到的信号自动飞行。 第一和第二任务计算机利用从第一或第二传感器装置检测到的信号来控制第一和第二自动飞行装置中的一个。 第一仿真部分模拟第一传感器装置和第一自动飞行装置上的信息。 第二仿真部分模拟第二传感器装置和第二自动飞行装置上的信息。 独立计量器显示独立于第一和第二传感器装置的飞行信息。 操作选择开关以忽略从超过预定阈值阀的传感器装置之一传输的信号。
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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：KR101302493B1
公开(公告)日：2013-09-02
申请号：KR1020120041872
申请日：2012-04-23
Applicant: 국방과학연구소
Abstract: PURPOSE: A helicopter intercom device equipped with a noise cancelling function and a method thereof are provided to remove noises mixed in an audio signal during internal communications between a pilot and a crew member, thereby enabling internal communications between the pilot and the crew member to be accurately performed. CONSTITUTION: A communications repeater (400) is connected with a user terminal. The communications repeater internally or externally relays the communications of a signal from the user terminal. A two-way radio (500) is connected with the communications repeater. The two-way radio transmits and receives a signal to and from the outside for the communications repeater. An external control center (100) is wirelessly connected with the two-way radio. The external control center transmits and receives a signal to and from the two-way radio. [Reference numerals] (100) External control center; (210) User device 1; (220) User device 2; (230) User device 3; (240) User device 4; (400) Communications repeater; (500) Two-way radio
Abstract translation: 目的：提供一种配备有噪声消除功能的直升机对讲设备及其方法，以在飞行员和乘务员之间的内部通信期间消除在音频信号中混合的噪声，从而使飞行员和乘务员之间的内部通信成为 准确执行。 构成：通信中继器（400）与用户终端连接。 通信中继器内部或外部中继来自用户终端的信号的通信。 双向无线电（500）与通信中继器连接。 双向无线电发送和接收来自外部的用于通信中继器的信号。 外部控制中心（100）与双向无线电无线连接。 外部控制中心向双向无线电收发信号。 （附图标记）（100）外控中心; （210）用户装置1; （220）用户设备2; （230）用户设备3; （240）用户设备4; （400）通讯中继器; （500）双向无线电
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公开(公告)号：KR1020140124890A
公开(公告)日：2014-10-28
申请号：KR1020120042482
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 laser displacement sensor, capable of quickly, accurately, and automatically measuring the internal crack state and corroded position and depth of a bore using laser beams 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 depth of the bore using a prism rotation body (130), the color CCD image sensor (120), and a laser displacement sensor (150); and a control device (200) for processing and revealing all kinds of data transmitted from the measurement device body (100), and remote-controlling the measurement device body (100). Accordingly, the present invention can inspect the bore faster and more accurately than an existing way for operating mechanical or electromechanical equipment, and can reveal and determine the internal state of the bore almost in real time.
Abstract translation: 本发明涉及一种用于使用激光位移传感器测量孔的腐蚀的装置，其能够使用激光束和CCD图像传感器快速准确地并且自动地测量内部裂纹状态和孔的腐蚀位置和深度。 该装置包括：测量装置主体（100），其在枪筒（400）的孔（410）中线性移动，并且使用棱镜旋转体（130）测量内部裂纹状态和孔的腐蚀位置和深度， 彩色CCD图像传感器（120）和激光位移传感器（150）; 以及用于处理和显示从测量装置主体（100）发送的各种数据的遥控装置（200），以及远程控制测量装置主体（100）。 因此，本发明可以比用于操作机械或机电设备的现有方式更快更准确地检查钻孔，并且可以几乎实时地显示和确定孔的内部状态。
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Patent Agency Ranking
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：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：KR1020140090476A
公开(公告)日：2014-07-17
申请号：KR1020130002577
申请日：2013-01-09
Applicant: 국방과학연구소
CPC classification number: G09B9/42 , G09B9/44 , G09B9/46 , G09B19/165
Abstract: According to an embodiment of the present invention, an aircraft with a training system includes a plurality of multifunctional displays which display flight-related data to a user; and a control unit which controls devices in the aircraft based on user inputs and outputs data from the devices onto the multifunctional displays. In a first mode, the control unit actually controls the devices in the aircraft. In a second mode, the control unit virtually controls the devices in the aircraft, and the result data according to user inputs is outputted onto the multifunctional displays.
Abstract translation: 根据本发明的实施例，具有训练系统的飞机包括多个多功能显示器，其向用户显示飞行相关数据; 以及控制单元，其基于用户输入来控制飞行器中的设备，并将来自设备的数据输出到多功能显示器上。 在第一模式中，控制单元实际控制飞行器中的装置。 在第二模式中，控制单元虚拟地控制飞行器中的装置，并将根据用户输入的结果数据输出到多功能显示器上。
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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：KR101480861B1
公开(公告)日：2015-01-13
申请号：KR1020120042482
申请日：2012-04-24
Applicant: 국방과학연구소
IPC: G01N21/954 , G01B11/16 , F41A31/00
Abstract: 본 발명은 레이저 빔과 CCD 이미지 센서를 이용하여 신속 정확하게 포강 내부의 균열 상태와 마모 위치 및 그 깊이를 자동으로 측정할 수 있도록 한 레이저 변위 센서를 이용한 포강마모 측정장치에 관한 것으로서,
포신(400)의 포강(410) 내부에서 직선 이동하며, 프리즘 회전체(130)와 컬러 CCD 이미지 센서(120) 및 레이저 변위 센서(150)를 이용하여 포강 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.
이에 따라 기계식 또는 전기-기계식 장비를 운용하는 종래 방식에 비해 보다 신속하고 정확하게 포강 검사를 수행할 수 있으며, 거의 실시간으로 포강 내부의 상태를 시현 및 판정할 수 있게 된다.
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