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公开(公告)号：KR1020150019917A
公开(公告)日：2015-02-25
申请号：KR1020130097362
申请日：2013-08-16
Applicant: 한국항공우주연구원
CPC classification number: G06F17/5086 , G06F17/5095
Abstract: 본 발명에 따르면, 힘전달 경로 상의 기계적 요소와 고립된 유압작동유기둥의 개별 강성값의 조합을 이용하여 상기 서보구동기(2)가 갖는 무한주파수 강성을 예측 및 설계하는 단계(S210); 인장 및 압축부하 경로 상에 위치하는 단순한 기계적 형상 구동기 구성요소의 개수를 고려하여 초기 구성요소의 등가강성값을 할당하고 해석식에 의하여 구성요소의 주요 치수를 설계하는 단계(S230); 구동기 해당 구성요소에 의하여 설계된 확장 및 수축 유압격실 작동유기둥의 등가강성값을 설계하는 단계(S250); 및 설계한 기계적 구성요소들과 작동유기둥의 등가강성을 조합하여 구동기의 무한주파수 강성값을 설계하는 단계(S270);를 포함하는 제어강성 요구조건을 충족시키는 구동기 설계기법을 개시한다.
Abstract translation: 根据本发明，公开了一种满足控制刚度要求的致动器的设计方法。 本发明包括以下步骤：通过使用力传递路径上的机械元件和隔离液压操作流体柱的单独刚度值的组合来估计和设计伺服致动器（2）具有的无限频率刚度（S210） ; 考虑位于张力和压缩载荷路径上的简单机械形状致动器部件的数量来分配初始部件的等效刚度值（S230）; 设计由相应的执行器部件设计的延伸和收缩液压分隔操作液柱的等效刚度值（S250）; 通过组合操作流体柱的等效刚度和设计的机械部件来设计致动器的无限频率刚度值（S270）。
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公开(公告)号：KR1020150019918A
公开(公告)日：2015-02-25
申请号：KR1020130097363
申请日：2013-08-16
Applicant: 한국항공우주연구원
IPC: G06F17/50
CPC classification number: G06F17/5086
Abstract: 본 발명에 따르면, 힘전달 경로 상의 기계적 요소와 고립된 유압작동유기둥의 개별 강성값의 조합을 이용하여 상기 서보구동기(2)가 갖는 무한주파수 강성을 예측하는 무한주파수 강성 측정부; 인장 및 압축부하 경로 상에 위치하는 단순한 기계적 형상 구동기 구성요소의 개수를 고려하여 초기 구성요소의 등가강성값을 할당하고 해석식에 의하여 구성요소의 주요 치수를 설계하는 치수설계부; 구동기 해당 구성요소에 의하여 설계된 확장 및 수축 유압격실 작동유기둥의 등가강성값을 설계하는 등가강성값 설계부; 및 설계한 기계적 구성요소들과 작동유기둥의 등가강성을 조합하여 구동기의 무한주파수 강성값을 설계하는 무한주파수 강성설계부;를 포함하는 제어강성 요구조건을 충족시키는 구동기 설계시스템을 개시한다.
Abstract translation: 根据本发明，公开了一种满足控制刚度要求的致动器的设计系统。 本发明包括无限频率刚度测量单元，其通过使用力传递路径上的机械元件与分离的液压操作流体的单独刚度值的组合来估计伺服致动器（2）包括的无限频率的强度 柱; 考虑到位于张力和压缩载荷路径上的简单机械形状致动器部件的数量，分配初始部件的等效刚度值的尺寸设计单元，并通过分析公式设计部件的主要尺寸; 设计由对应的致动器部件设计的延伸和收缩液压分隔操作流体柱的等效刚度值的等效刚度值设计单元; 以及无限频率刚度设计单元，通过组合操作流体柱的等效刚度和设计的机械部件来设计致动器的无限频率刚度值。
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公开(公告)号：KR1020100079806A
公开(公告)日：2010-07-08
申请号：KR1020080138381
申请日：2008-12-31
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A device and a method for measuring thrust are provided to accurately measure thrust even if a shaft for a thruster is not the same as a shaft for the device and to easily obtain calibration data for measuring thrust. CONSTITUTION: A device for measuring thrust comprises a thruster adapter(110), a second base(120), a measuring load cell(130), a calibrating load cell, and a controller. The thruster adapter is composed of a fixing member which fixes a thruster(200). The second base is installed in the bottom of the thruster adapter and is horizontally moved on a first base. The measuring load cell has a measuring load cell bar and a measuring adapter. The calibrating load cell gas a calibrating load cell bar(141) and a calibration adapter(143). The controller calculates and corrects an error value of the measuring load cell.
Abstract translation: 目的：提供一种用于测量推力的装置和方法，用于精确测量推力，即使用于推进器的轴不同于用于该装置的轴并且容易地获得用于测量推力的校准数据。 构成：用于测量推力的装置包括推进器适配器（110），第二基座（120），测量称重传感器（130），校准称重传感器和控制器。 推进器适配器由固定推进器（200）的固定构件组成。 第二基座安装在推进器适配器的底部，并在第一基座上水平移动。 测量称重传感器具有测量称重传感器杆和测量适配器。 校准称重传感器气体校准称重传感器杆（141）和校准适配器（143）。 控制器计算并校正测量称重传感器的误差值。
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公开(公告)号：KR100370745B1
公开(公告)日：2003-02-05
申请号：KR1020000069068
申请日：2000-11-20
Applicant: 한국항공우주연구원
IPC: G09B9/52
Abstract: PURPOSE: A uniaxial simulator for a rocket posture control simulation is provided to be able to previously estimate the capacity of a control system via the simulation performed on the ground in view of various dangerous factors. CONSTITUTION: The uniaxial simulator for a rocket posture control simulation comprises: a horizontal stand(10); a thrust system located on the horizontal stand; a balancing ring(12) installed under the horizontal stand for setting the moment of inertia of a whole system, and pulling down the center of gravity; a balance member(13) installed at the side surface of the balancing ring; an air bearing system connected to the horizontal stand by using a shaft; an angular velocity sensor; a control box for controlling the operation of the trust system by comparing supplied power with input power and converting all output signals into voltage values within a desired range; a ground control box; and a real time computer system.
Abstract translation: 目的：提供用于火箭姿态控制模拟的单轴模拟器，以便能够根据各种危险因素预先通过在地面上进行的模拟来估计控制系统的容量。 构成：用于火箭姿态控制模拟的单轴模拟器包括：水平支架（10）; 位于水平支架上的推力系统; 安装在水平支架下方的平衡环（12），用于设定整个系统的惯性矩，并降低重心; 平衡构件（13），其安装在平衡环的侧表面处; 通过使用轴连接到水平支架的空气轴承系统; 角速度传感器; 控制箱，用于通过比较所提供的功率与输入功率来控制信任系统的操作，并将所有输出信号转换为期望范围内的电压值; 地面控制箱; 和一个实时计算机系统。
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公开(公告)号：KR101520693B1
公开(公告)日：2015-05-18
申请号：KR1020130097363
申请日：2013-08-16
Applicant: 한국항공우주연구원
IPC: G06F17/50
Abstract: 본발명에따르면, 힘전달경로상의기계적요소와고립된유압작동유기둥의개별강성값의조합을이용하여상기서보구동기(2)가갖는무한주파수강성을예측하는무한주파수강성측정부; 인장및 압축부하경로상에위치하는단순한기계적형상구동기구성요소의개수를고려하여초기구성요소의등가강성값을할당하고해석식에의하여구성요소의주요치수를설계하는치수설계부; 구동기해당구성요소에의하여설계된확장및 수축유압격실작동유기둥의등가강성값을설계하는등가강성값설계부; 및설계한기계적구성요소들과작동유기둥의등가강성을조합하여구동기의무한주파수강성값을설계하는무한주파수강성설계부;를포함하는제어강성요구조건을충족시키는구동기설계시스템을개시한다.
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Patent Agency Ranking
公开(公告)号：KR1020090068718A
公开(公告)日：2009-06-29
申请号：KR1020070136445
申请日：2007-12-24
Applicant: 한국항공우주연구원
Abstract: An anti-surging pneumatic valve is provided to prevent damage or malfunction of pneumatic parts in a pneumatic system due to the surge pressure produced when opening a gas storage tank containing high pressure gas. An anti-surging pneumatic valve(100) is connected to a gas storage tank in which high pressure gas is contained, and includes a body(150), a plunger(110), an elastic member(112), and an anchoring bolt(130). The body is composed of an upper body(160) and a lower body(170). The plunger is positioned in the center of a through hole formed inside the upper body and has a protruding rod(113) in the central portion. The plunger is pressed downward by surge pressure flowing into the upper body and closed onto the top of a poppet(120) so that the surge pressure is blocked from flowing into the lower body. The elastic member is inserted through the protruding rod of the plunger and has elasticity for dampen the impact resulting from the contact between the plunger and the poppet and return the plunger to the original position. The anchoring bolt connects the upper and lower bodies to fix, and supports the bottom of the poppet. The poppet is fixed to the inside surface of the through hole of the upper body and supports the bottom of the elastic member.
Abstract translation: 提供防喘振气动阀，以防止由于在打开包含高压气体的储气罐时产生的浪涌压力而在气动系统中气动部件的损坏或故障。 防喘振气动阀（100）与容纳高压气体的储气罐连接，包括主体（150），柱塞（110），弹性部件（112）和锚定螺栓（ 130）。 身体由上身（160）和下身（170）构成。 柱塞位于形成在上体内部的通孔的中心，并且在中心部分具有突出的杆（113）。 柱塞被流入上体的冲击压力向下按压并且关闭到提升阀（120）的顶部，使得喘振压力被阻止流入下体。 弹性构件穿过柱塞的突出杆插入并且具有弹性，用于抑制由柱塞和提升阀之间的接触产生的冲击并将柱塞返回到原始位置。 锚固螺栓连接上部和下部主体以固定，并支撑提升阀的底部。 提升头固定在上身的通孔的内表面并支撑弹性构件的底部。
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公开(公告)号：KR1020050008568A
公开(公告)日：2005-01-21
申请号：KR1020040108883
申请日：2004-12-20
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A posture measurement system of a non-contact typed triaxial simulator is provided to obtain the exact position and posture information by precisely measuring the position and the posture of the triaxial simulator. CONSTITUTION: A posture measurement system contains an air bearing system, a coordinate plate(60), a camera(70) and a computer(80). The air bearing system comprises air-lift typed air bearing balls(20), a simulator(10) connected with rotation shafts(30) of the air bearing balls and a simulator support(50) to include three laser pointers(40). The coordinate plate is installed in the same direction as the rotation shafts outside the air bearing system. The camera photographs an image of the laser pointer on the coordinate plate by installing outside the air bearing system. The computer calculates the position and the posture of the simulator by using the image information from the camera.
Abstract translation: 目的：提供非接触型三轴模拟器的姿态测量系统，通过精确测量三轴模拟器的位置和姿势，获得准确的位置和姿势信息。 构成：姿势测量系统包括空气轴承系统，坐标板（60），相机（70）和计算机（80）。 空气轴承系统包括气升式空气轴承滚珠（20），与空气轴承滚珠的旋转轴（30）连接的模拟器（10）和包括三个激光指针（40）的模拟器支架（50）。 坐标板与空气轴承系统外的旋转轴方向相同。 摄像机通过安装在空气轴承系统外面，将坐标盘上的激光指示器的图像拍摄。 计算机通过使用来自相机的图像信息来计算模拟器的位置和姿势。
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公开(公告)号：KR101054734B1
公开(公告)日：2011-08-08
申请号：KR1020080138381
申请日：2008-12-31
Applicant: 한국항공우주연구원
Abstract: 본 발명에 따르면, (a) 추력 발생 축(L
1 )과 추력 측정 축(L
2 )이 평행한 상태로 추력기 어뎁터의 접합면에 추력기의 장착면을 장착하는 추력기 장착 단계; (b) 측정로드셀부의 측정어뎁터를 회전시켜 상기 측정어텝터의 일단부와 측정로드셀을 서로 접촉시키는 측정어뎁터 조절 단계; (c) 상기 측정로드셀 및 교정로드셀의 입력값을 초기화하는 입력값 초기화 단계; (d) 상기 추력기의 일측에 교정어뎁터를 고정 설치한 상태에서, 상기 교정어뎁터의 길이조절부를 단계별로 회전시켜 상기 측정로드셀 및 교정로드셀에 힘을 주입하여, 상기 측정로드셀 및 교정로드셀에 작용하는 힘값을 측정하는 힘값 측정 단계; (e) 상기 측정로드셀 및 교정로드셀에서 측정된 각 단계별 힘값을 기초로 하여, 상기 측정로드셀의 오차값을 산출 및 교정하는 오차값 산출 및 교정 단계; (f) 상기 추력기의 일측에서 교정어뎁터를 분리시킨 상태에서 상기 추력기를 가동하여, 상기 측정로드셀로 전달되는 상기 추력기의 추력을 측정하는 추력 측정 단계;를 포함하는 추력 측정 방법을 개시한다.
추력, 추력기, 베이스Abstract translation: 根据本发明，（a）推力产生轴线L.
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公开(公告)号：KR100445680B1
公开(公告)日：2004-08-25
申请号：KR1020010078349
申请日：2001-12-12
Applicant: 한국항공우주연구원
IPC: B64G3/00
Abstract: PURPOSE: A thrust measurer of a cold gas thruster is provided to design a stable position controller by measuring the thrust and the response characteristic of the thruster. CONSTITUTION: A sliding rod(6) is connected with a horizontal support(4) by protruding from three directions of a fixing support. A thruster(20) is connected with the center of the horizontal support. The thruster is fixed on a support(21) to be connected through a rod(22). A seal(12) is connected with a calibration support(11) under the fixing support by connecting with both sides of the horizontal support. A load cell(7) is installed in the center of the fixing support. Thereby, an exact thrust is measured though the weight of the thruster is changed.
Abstract translation: 目的：通过测量推进器的推力和响应特性，提供冷气推进器的推力测量器来设计稳定的位置控制器。 组成：滑杆（6）通过从固定支架的三个方向突出而与水平支架（4）连接。 推进器（20）与水平支撑件的中心连接。 推力器固定在支撑件（21）上以通过杆（22）连接。 密封件（12）通过与水平支撑件的两侧连接而在固定支撑件下方与校准支撑件（11）连接。 称重传感器（7）安装在固定支架的中心。 因此，尽管推进器的重量发生了变化，但仍可以测量确切的推力。
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公开(公告)号：KR1020030048299A
公开(公告)日：2003-06-19
申请号：KR1020010078349
申请日：2001-12-12
Applicant: 한국항공우주연구원
IPC: B64G3/00
Abstract: PURPOSE: A thrust measurer of a cold gas thruster is provided to design a stable position controller by measuring the thrust and the response characteristic of the thruster. CONSTITUTION: A sliding rod(6) is connected with a horizontal support(4) by protruding from three directions of a fixing support. A thruster(20) is connected with the center of the horizontal support. The thruster is fixed on a support(21) to be connected through a rod(22). A seal(12) is connected with a calibration support(11) under the fixing support by connecting with both sides of the horizontal support. A load cell(7) is installed in the center of the fixing support. Thereby, an exact thrust is measured though the weight of the thruster is changed.
Abstract translation: 目的：提供冷气推进器的推力测量器，通过测量推力器的推力和响应特性来设计稳定的位置控制器。 构成：滑动杆（6）通过从固定支撑件的三个方向突出而与水平支撑件（4）连接。 推进器（20）与水平支架的中心连接。 推进器固定在支撑件（21）上以通过杆（22）连接。 密封件（12）通过与水平支撑件的两侧连接而与固定支撑件下方的校准支撑件（11）连接。 称重传感器（7）安装在固定支架的中心。 因此，通过改变推进器的重量来测量精确的推力。
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