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公开(公告)号：KR100472968B1
公开(公告)日：2005-03-08
申请号：KR1020020067879
申请日：2002-11-04
Applicant: 한국항공우주연구원
IPC: B64C13/16
Abstract: 본 발명은 고도 20Km 이상까지 상승하여 운영되는 대형 무인비행선에 장치되는 시스템 구성요소 중 지상 조종사에 의한 무선조종명령 없이 길이 40m 이상인 대형비행선이 자체적인 판단아래 이륙과 착륙을 자율적으로 용이하게 할 수 있는 자동 이·착륙 비행장치에 관한 것이다.
이러한 본 발명은 길이 40m 이상의 대형 무인비행선(101)과 대형비행선 조종을 위한 승강키(102), 방향키(103), 조종면엑추에이터(104)(107)를 수직꼬리날개(105) 및 수평꼬리날개(106)에 장치하고, 추력을 내는 프로펠러(107)와 추력방향조종을 위한 틸팅시스템(201) 및 속도측정을 위한 속도계(109), 위치 및 고도정보 획득을 위한 GPS 수신기(110), GPS 안테나(111) 및 레이져 고도계(112), 비행선의 동운동 비행값 측정을 위한 관성항법센서(113)로 구성되며, 자동이륙과 착륙을 위한 자동이착륙프로그램(210)이 곤돌라(115)내부에 장착된 비행조종컴퓨터(200)내에 설치됨으로써 이루어진다.-
公开(公告)号：KR100456905B1
公开(公告)日：2004-11-10
申请号：KR1020020073779
申请日：2002-11-26
Applicant: 한국항공우주연구원
IPC: B64C1/36
Abstract: PURPOSE: A valve is opened by generating a force disproportional to the valve stroke by using a permanent magnet and a magnetic body. CONSTITUTION: In a valve to open/close a valve disk(9) operating a central link(10) by a spring(5) and a link(4), a magnetic body(2) is installed in upper part of the central link. A permanent magnet(1) is installed in upper part of the magnetic body, and is positioned at a link frame(3). When an inner pressure of the aircraft reaches a certain value, the valve is opened to its utmost stroke. When the pressure is reduced, the valve is closed.
Abstract translation: 目的：通过使用永磁体和磁体产生与阀行程不成比例的力来打开阀。 本发明涉及一种在通过弹簧（5）和连杆（4）操作中央连杆（10）的阀盘（9）中打开/关闭阀盘（9）的阀门，磁体（2）安装在中央连杆 。 永磁体（1）安装在磁体的上部，并位于连杆架（3）处。 当飞机的内部压力达到一定值时，阀门打开到最大行程。 当压力降低时，阀门关闭。
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公开(公告)号：KR1020040043926A
公开(公告)日：2004-05-27
申请号：KR1020020072391
申请日：2002-11-20
Applicant: 한국항공우주연구원
IPC: B64C13/18
CPC classification number: G08G5/0069 , B64B1/62 , B64B1/64 , B64C2201/022 , B64C2201/141 , B64D2045/0085 , G05D1/0011
Abstract: PURPOSE: A flight finishing system of an unmanned aircraft is provided to forcibly land the aircraft by discharging helium gas with opening the helium valve when the large unmanned aircraft gets out of control from communication interruption or defect. CONSTITUTION: A flight finishing system is composed of a ground control tower(200) transmitting the emergency descent command to a large unmanned aircraft in requiring emergency landing; a defect detecting unit(120) loaded in the unmanned aircraft to output a defect sensing signal by detecting fault of power, communication and control; a flight end system(110) commanding the end of flight in detecting the emergency descent command of the ground control tower and the defect sensing signal of the defect detecting unit; and an operating unit(130) discharging helium gas by opening the helium valve according to the command of the flight end system.
Abstract translation: 目的：提供无人驾驶飞机的飞行整理系统，以便在大型无人驾驶飞机失控以防止通信中断或缺陷时，通过氦气排放氦气强制着陆飞机。 规定：飞行整理系统由地面控制塔（200）组成，将紧急下降指令传送到需要紧急降落的大型无人飞机; 通过检测电力故障，通信和控制，装载在无人机中的缺陷检测单元（120）输出缺陷感测信号; 指示飞行结束的飞行终端系统（110），用于检测地面控制塔的紧急下降命令和缺陷检测单元的缺陷感测信号; 以及操作单元（130），其根据飞行终端系统的命令打开氦气阀来排出氦气。
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公开(公告)号：KR1020000067382A
公开(公告)日：2000-11-15
申请号：KR1019990015141
申请日：1999-04-28
Applicant: 한국항공우주연구원
IPC: B64B1/10
Abstract: PURPOSE: An airship direction control system is provided to control the direction of an airship by periodically varying the current speed of a propeller and asymmetrically generating the rear current speed of the propeller. CONSTITUTION: Blades(8,8'), rods(10,10') for varying a pitch angle and an upper plate(11) for controlling a variable pitch angle rotate with a rotary shaft(7). A lower plate(12) for controlling a variable pitch angle does not rotate. In this state, when inclination is applied in a desired direction, the length of the rods(10,10') is fixed so that the pitch angle of the blades(8,8') is varied. In addition, in equally varying the pitch angle of the blades, a collective pitch angle increase plate(13) is moved along a rotary shaft(7).
Abstract translation: 目的：提供飞艇方向控制系统，以通过周期性地改变螺旋桨的当前速度并且不对称地产生螺旋桨的后方当前速度来控制飞艇的方向。 构成：用于改变桨距角的叶片（8,8'），杆（10,10'）和用于控制可变桨距角的上板（11）与旋转轴（7）一起旋转。 用于控制可变桨距角的下板（12）不旋转。 在这种状态下，当沿期望的方向施加倾斜时，杆（10,10'）的长度被固定，使得叶片（8,8'）的俯仰角变化。 此外，在等效地改变叶片的俯仰角的同时，沿着旋转轴（7）移动集体俯仰角增加板（13）。
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Patent Agency Ranking
公开(公告)号：KR100648466B1
公开(公告)日：2006-11-27
申请号：KR1020050117935
申请日：2005-12-06
Applicant: 한국항공우주연구원
Abstract: A bank control system for an airship is provided to control bank of the airship by varying the position of a gondola of the airship and changing the center of the gravity of the airship to achieve the optimum bank angle for more solar energy. In a bank control system for an airship, a rail(30) is horizontally installed inside a gasbag(11) or on the outer peripheral surface of lower part of the gas bag. A wheel generates the bank in the airship by horizontally moving a gondola(20) connected to the rail. A wheel driving part(40) is connected to the wheel and drives the wheel. And a wheel driving controller is electrically connected to the wheel driving part and controls the wheel driving part.
Abstract translation: 提供飞艇的银行控制系统，通过改变飞艇的吊舱的位置并改变飞艇的重心以实现更多太阳能的最佳银行角度来控制飞艇的银行。 在飞艇的岸上控制系统中，导轨（30）水平地安装在气囊（11）内或气囊下部的外周表面上。 通过水平移动与轨道连接的吊舱（20），轮子在飞艇中产生岸。 车轮驱动部分（40）连接到车轮并驱动车轮。 并且车轮驱动控制器电连接到车轮驱动部件并且控制车轮驱动部件。
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公开(公告)号：KR100587791B1
公开(公告)日：2006-06-09
申请号：KR1020040102745
申请日：2004-12-08
Applicant: 한국항공우주연구원
IPC: H04B1/40
Abstract: 본 발명은 고주파신호를 송수신하는 레이더나 통신 시스템에서 송수신용 중간주파수를 자동으로 조절할 수 있는 장치를 제공하는 것으로, 입력되는 초단파발진 조절용 전압의 크기에 비례하는 초단파 주파수를 발진하기 위한 국부 발진기; 외부로부터 수신되는 고주파신호를 국부 발진기로부터 발진되는 초단파 주파수와 혼합하여 고주파신호를 초단파 주파수에 비례하는 중간주파수신호로 변환시켜 출력하는 제 1 중간주파수 처리기; 고주파 발진기로부터 발진되는 고주파신호를 국부 발진기로부터 발진되는 초단파 주파수와 혼합하여 고주파신호를 초단파 주파수에 비례하는 중간주파수로 변환시키고, 변환한 중간주파수를 전압으로 변환시켜 출력하는 제 2 중간주파수 처리기; 제 2 중간주파수 처리기로부터 출력되는 전압의 크기에 따라 국부 발진기의 초단파 발진을 제어하기 위한 제어신호를 출력하는 제어신호 발생기; 및 제어신호 발생기로부터 발생되는 제어신호에 따라 초단파발진 조절용 전압을 국부 발진기로 출력하는 초단파발진 조절기를 포함한다.
고주파, 중간주파수, 조절, 송수신, 레이더Abstract translation: 本发明的本地振荡器是提供一种装置，其可以自动地调整中心频率用于在雷达或通信系统用于发送和接收的高频信号，将微波振荡频率正比于微波振荡器的尺寸，用于调整所述电压输入的发送和接收; 第一中频处理器，其在与被从外部接收通过所述本地振荡器的输出并转换为中频信号，该信号正比于高频信号的微波频率的高频信号的微波振荡频率组合; 用于混合微波频率振荡器从来自本地振荡器的高频振荡器振荡出的高频信号的第二中频处理器被转换为成比例的高频信号与所述微波频率，中频转换成中频，该电压转换为输出; 控制信号发生器，用于根据从第二中频处理器输出的电压的大小输出用于控制本地振荡器的微波振荡的控制信号; 以及微波振荡控制器，用于根据从控制信号发生器产生的控制信号将微波振荡控制电压输出到本地振荡器。
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公开(公告)号：KR1020040039117A
公开(公告)日：2004-05-10
申请号：KR1020020067879
申请日：2002-11-04
Applicant: 한국항공우주연구원
IPC: B64C13/16
CPC classification number: B64B1/00 , B64C2201/022 , B64C2201/141 , B64D43/00 , G05D1/102
Abstract: PURPOSE: An automatic take-off and landing system for a large-class unmanned airship is provided to easily perform a takeoff and a landing under the self decision. CONSTITUTION: An elevator(102), a rudder(103), and flight control surface actuators(104,107) for handling the large-class unmanned airship over 40m in size are mounted to a vertical tail(105) and a horizontal tail(106). An automatic take-off and landing system for a large-class unmanned airship comprises a propeller(108) generating a thrust; a tilting system for handling the thrust direction; a speedometer for measuring the speed; a GPS(Global Positioning System) receiver(110), a GPS antenna(111), and a laser altimeter(112) for taking the position and height information; and an inertial navigation sensor(113).
Abstract translation: 目的：提供大型无人飞艇的自动起飞和着陆系统，以便在自我决定下轻松进行起飞和着陆。 构成：用于处理尺寸超过40m的大型无人飞艇的电梯（102），方向舵（103）和飞行控制表面致动器（104,107）安装到垂直尾部（105）和水平尾部（106） 。 用于大型无人飞艇的自动起飞和着陆系统包括产生推力的螺旋桨（108） 用于处理推力方向的倾斜系统; 用于测量速度的速度计; GPS（全球定位系统）接收器（110），GPS天线（111）和用于获取位置和高度信息的激光高度计（112） 和惯性导航传感器（113）。
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公开(公告)号：KR1020030056405A
公开(公告)日：2003-07-04
申请号：KR1020010086609
申请日：2001-12-28
Applicant: 한국항공우주연구원
IPC: G01N3/12
Abstract: PURPOSE: A testing apparatus of a component of an envelope for an airship is provided to operate a layer pressure test in a bi-axial loading condition generated by internal pressure. CONSTITUTION: A testing apparatus of a component of an envelope for an airship comprises a pulling device(1) and a circular press device(2). A pulley fixing plate(9) and an actuator(5) are installed to a fixed beam(4) formed to the inside of a base. A string connected to a patch of a testing layer(18) installed to a fixing ring(8) of a testing member penetrates a pulley to connect to the actuator. Therein, the pulling device operates a strength test of the patch. A press shaft(15) is connected to a connecting rod(13') of a press ring(13) formed to a rear portion of the fixing ring of the testing member, and the press shaft passes through a shaft supporter(14). Therein, the circular press device operates a layer pressure test. Consequently, the strength test of the patch and the layer pressure test are operated fast and conveniently at the same time.
Abstract translation: 目的：提供用于飞艇的信封的部件的测试装置，以在由内部压力产生的双轴加载条件下操作层压试验。 构成：用于飞艇的信封的部件的测试装置包括拉动装置（1）和圆形压制装置（2）。 滑轮固定板（9）和致动器（5）安装到形成于底座内部的固定梁（4）上。 连接到安装到测试构件的固定环（8）的测试层（18）的贴片的弦穿透滑轮以连接到致动器。 其中，牵引装置进行贴片的强度测试。 压轴（15）连接到形成在测试构件的固定环的后部的压环（13）的连杆（13'），并且压轴穿过轴支撑件（14）。 其中，圆压机装置进行层压试验。 因此，贴片的强度试验和层压试验同时快速方便地进行。
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公开(公告)号：KR1020030050310A
公开(公告)日：2003-06-25
申请号：KR1020010080723
申请日：2001-12-18
Applicant: 한국항공우주연구원
IPC: B64C39/00
CPC classification number: B64B1/58 , B64C39/02 , B64C2201/022
Abstract: PURPOSE: An envelope structure is provided to prevent the sudden inclination of helium and the large change of a helium volume ratio by a simple structure. CONSTITUTION: A front partition(2) and a rear partition(3) divide the inside of a plane(1) to three parts. Separating films(7,8,9) are installed in the center of the front partition and the rear partition. A front helium envelope(4), a middle helium envelope(5) and a rear helium envelope(6) are divided in the upper part and a front air envelope(10), and a middle air envelope(11) and a rear air envelope(12) are divided by the separating films. Thereby, the sudden inclination of helium and the large change of a helium volume ratio are prevented.
Abstract translation: 目的：提供一种包络结构，通过简单的结构防止氦的突然倾斜和氦体积比的大的变化。 构成：前隔板（2）和后隔板（3）将平面（1）的内部分成三部分。 分隔膜（7,8,9）安装在前隔板和后隔板的中心。 前氦气封（4），中氦气囊（5）和后氦气囊（6）被分成上部和前部气囊（10），中部空气气囊（11）和后部空气 信封（12）被分离膜分隔。 从而防止氦的突然倾斜和氦体积比的大的变化。
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