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公开(公告)号：KR100436178B1
公开(公告)日：2004-06-16
申请号：KR1020020050002
申请日：2002-08-23
Applicant: 한국항공우주연구원
IPC: B64D27/24
CPC classification number: Y02T50/62
Abstract: PURPOSE: An aircraft propulsion system using electric energy is provided to improve responsiveness by detecting the present condition of the propulsion system accurately and quickly with a propulsion controller. CONSTITUTION: An aircraft propulsion system comprises a gas turbine engine(3) driving by receiving fuel from a fuel tank(2); a generator(4) connected to a rotating shaft of the gas turbine engine to generate power; a power control unit(5) supplying power from the generator to units with converting properly, performing self-diagnosis on output of the generator and load connection, and supplying electric energy by automatically converting into the emergency battery in cutting off power; a propulsion controller(6) transmitting the command to units by receiving signals from a flight control unit(7), and transmitting information on the propulsion system to the flight control unit; the flight control unit transmitting information from the propulsion controller to a pilot, and controlling the propulsion controller; a motor driver(8) regulating rpm and output of a main motor(9) according to the control signal by receiving power from the power control unit; a tilt servo motor(10) driving a thrust vector controller according to the control signal by receiving power; a start battery(11) starting the engine according to the control signal; an emergency battery(12) supplying minimum power till landing in cutting off main power; a battery charger/discharger(13) charging and discharging the batteries; and an ECU(14) controlling the engine to receive power by transmitting information to the gas turbine engine, and transmitting the state of the gas turbine engine to the propulsion controller.
Abstract translation: 目的：提供一种利用电能的飞机推进系统，以通过推进控制器准确快速地检测推进系统的当前状况来提高响应性。 构成：飞机推进系统包括通过接收来自燃料箱（2）的燃料驱动的燃气涡轮发动机（3）; 与燃气涡轮发动机的旋转轴连接并发电的发电机（4） 功率控制单元（5），用于从发电机向正常转换的单元供电，对发电机的输出和负载连接进行自诊断，并通过在切断电源时自动转换成应急电池来供应电能; 推进控制器（6），通过从飞行控制单元（7）接收信号向单元发送命令，并且将关于推进系统的信息传送给飞行控制单元; 所述飞行控制单元从所述推进控制器向驾驶员传输信息，并且控制所述推进控制器; 电动机驱动器（8），通过接收来自所述电力控制单元的电力，根据所述控制信号来调节主电动机（9）的转速和输出; 倾斜伺服电机（10），通过接收电力根据控制信号驱动推力矢量控制器; 根据控制信号启动发动机的启动电池（11） 应急电池（12），用于在切断主电源之前提供最小功率直到着陆; 电池充电器/放电器（13），对电池充电和放电; 和控制发动机通过向燃气涡轮发动机传输信息来接收动力并将燃气涡轮发动机的状态传输到推进控制器的ECU（14）。
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公开(公告)号：KR1020040018612A
公开(公告)日：2004-03-04
申请号：KR1020020050002
申请日：2002-08-23
Applicant: 한국항공우주연구원
IPC: B64D27/24
CPC classification number: Y02T50/62
Abstract: PURPOSE: An aircraft propulsion system using electric energy is provided to improve responsiveness by detecting the present condition of the propulsion system accurately and quickly with a propulsion controller. CONSTITUTION: An aircraft propulsion system comprises a gas turbine engine(3) driving by receiving fuel from a fuel tank(2); a generator(4) connected to a rotating shaft of the gas turbine engine to generate power; a power control unit(5) supplying power from the generator to units with converting properly, performing self-diagnosis on output of the generator and load connection, and supplying electric energy by automatically converting into the emergency battery in cutting off power; a propulsion controller(6) transmitting the command to units by receiving signals from a flight control unit(7), and transmitting information on the propulsion system to the flight control unit; the flight control unit transmitting information from the propulsion controller to a pilot, and controlling the propulsion controller; a motor driver(8) regulating rpm and output of a main motor(9) according to the control signal by receiving power from the power control unit; a tilt servo motor(10) driving a thrust vector controller according to the control signal by receiving power; a start battery(11) starting the engine according to the control signal; an emergency battery(12) supplying minimum power till landing in cutting off main power; a battery charger/discharger(13) charging and discharging the batteries; and an ECU(14) controlling the engine to receive power by transmitting information to the gas turbine engine, and transmitting the state of the gas turbine engine to the propulsion controller.
Abstract translation: 目的：提供使用电能的飞机推进系统，以通过用推进控制器准确，快速地检测推进系统的现状来提高响应性。 构成：飞机推进系统包括通过从燃料箱（2）接收燃料而驱动的燃气涡轮发动机（3）; 连接到所述燃气涡轮发动机的旋转轴以产生动力的发电机（4） 从发电机向正确转换的单元供电的电力控制单元（5），对发电机的输出和负载连接进行自诊断，以及通过在切断电力时自动转换为紧急电池来供电; 推进控制器（6），通过从飞行控制单元（7）接收信号将命令发送到单元，以及将关于推进系统的信息传送到飞行控制单元; 所述飞行控制单元将信息从所述推进控制器发送到飞行员，并且控制所述推进控制器; 电动机驱动器（8），其通过从所述功率控制单元接收电力来根据所述控制信号调节转速和主电动机（9）的输出; 倾斜伺服电动机（10），通过接收功率根据控制信号驱动推力矢量控制器; 启动电池（11），根据控制信号启动发动机; 紧急电池（12），其在切断主电源时提供最低功率直至着陆; 电池充电器/放电器（13）对电池充电和放电; 以及ECU（14），其通过向燃气涡轮发动机发送信息来控制发动机接收动力，并将所述燃气涡轮发动机的状态传递到所述推进控制器。
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公开(公告)号：KR1020030074002A
公开(公告)日：2003-09-19
申请号：KR1020020014207
申请日：2002-03-15
Applicant: 한국항공우주연구원
IPC: F16G11/12
CPC classification number: F16G11/12 , G01L1/2218
Abstract: PURPOSE: A turnbuckle having a load cell is provided to mount a mounting object to a specific site with a circular scale detecting plate and scale installed to a tip of a gap adjusting screw. CONSTITUTION: A gap adjusting screw(3,3') forming a ring(6,6') is assembled to a clamping nut(2,2') toward right and left directions. A circular scale indicating plate(4,4') is formed to an inner tip of the gap adjusting screw. Scale(5,5') is formed to a side of the clamping nut to indicate a gap. A tubular center portion(7) is formed to a middle portion of the clamping nut. A load cell(9) is composed of a strain gauge by processing an installing portion(8) from an upper side forming scale. The load cell is mounted to a turnbuckle(1). Therefore, a mounting object is mounted to a precise site by controlling a precise mounting site of the gap adjusting screw. Displacement of the gap adjusting screw and load on the clamping nut are measured by installing the load cell to the installing portion.
Abstract translation: 目的：提供一种具有称重传感器的螺丝扣，用于将安装对象安装到特定位置，并将圆形刻度检测板和刻度尺安装到间隙调节螺钉的尖端。 构成：形成环（6,6'）的间隙调节螺钉（3,3'）朝向左右方向组装到夹紧螺母（2,2'）。 在间隙调节螺钉的内端形成有圆周指示板（4,4'）。 刻度（5,5'）形成在夹紧螺母的一侧以指示间隙。 管状中心部分（7）形成在夹紧螺母的中间部分。 负载传感器（9）由应变计通过从上侧成形标尺处理安装部（8）构成。 称重传感器安装在螺丝扣（1）上。 因此，通过控制间隙调节螺钉的精确安装位置，将安装对象安装到精确位置。 通过将称重传感器安装到安装部分来测量间隙调节螺钉的位移和夹紧螺母上的负载。
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公开(公告)号：KR1020010066307A
公开(公告)日：2001-07-11
申请号：KR1019990067906
申请日：1999-12-31
Applicant: 한국항공우주연구원
IPC: G01N15/02
Abstract: PURPOSE: A technique for measuring spraying by using two light polarization is provided to measure a polarization ratio of scattering light beams from a liquid drop by using two color CCD cameras and two light beams of different colors having polarization perpendicular to each other, thereby measuring a size of the whole spraying in a short time at a low cost. CONSTITUTION: In a technique for measuring spraying by using two light polarization, a size of particles is measured with color CCD cameras(12,14) by using polarized dual light beams which have difference wave length from each other and are polarized perpendicularly to each other by passing through via a cylindrical lens(13) controlling a thickness and a mirror reflection plate(10) from a single sheet beam(9) generated by a cylindrical beam expander(8).
Abstract translation: 目的：提供一种通过使用两种光偏振来测量喷射的技术，以通过使用两个彩色CCD照相机和具有彼此垂直的偏振的两种不同颜色的光束来测量来自液滴的散射光的偏振比，从而测量 整个喷涂的尺寸在短时间内以低成本。 构成：在通过使用两个光偏振来测量喷涂的技术中，通过使用彼此具有差波长并且彼此垂直偏振的偏振双光束，用彩色CCD照相机（12,14）测量颗粒的尺寸 通过经由圆柱形扩束器（8）产生的单张片（9）经由控制厚度的柱面透镜（13）和镜反射板（10）穿过。
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公开(公告)号：KR1020070066528A
公开(公告)日：2007-06-27
申请号：KR1020050127814
申请日：2005-12-22
Applicant: 한국항공우주연구원
Abstract: A nozzle opening device for an engine test is provided to instantaneously open an air supply nozzle while maintaining the sealing state of the air supply nozzle in a restricted space. A nozzle opening device for an engine test includes a frame(110), a nozzle cover(120), a fixing cylinder, a catching member(130), and a cover support bar(140). The frame is located on the upper and lower sides of the nozzle. The nozzle cover is provided on the outlet side of the nozzle to regulate the opening/closing operation of the outlet. The fixing cylinder is formed in the frame on the upper side of the nozzle. The catching member is hinge-coupled to one end of the fixing cylinder. The catching member regulates the opening/closing operation of the nozzle cover by selectively supporting one side of the nozzle cover. One end of the cover is engaged with a portion of the nozzle cover and the other end thereof is hinge-coupled to a portion of the frame.
Abstract translation: 提供用于发动机试验的喷嘴打开装置，以便在保持空气供应喷嘴的密封状态在受限空间的同时瞬时打开供气喷嘴。 用于发动机试验的喷嘴打开装置包括框架（110），喷嘴盖（120），固定筒，捕获构件（130）和盖支撑杆（140）。 框架位于喷嘴的上侧和下侧。 喷嘴盖设置在喷嘴的出口侧，以调节出口的打开/关闭操作。 固定筒形成在喷嘴上侧的框架中。 捕捉构件铰接于固定筒的一端。 捕捉构件通过选择性地支撑喷嘴盖的一侧来调节喷嘴盖的打开/关闭操作。 盖的一端与喷嘴盖的一部分接合，并且其另一端铰链连接到框架的一部分。
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Patent Agency Ranking
公开(公告)号：KR100524497B1
公开(公告)日：2005-10-27
申请号：KR1020030094619
申请日：2003-12-22
Applicant: 한국항공우주연구원
IPC: B25B17/00
Abstract: 본 발명은 한번에 여러개의 볼트를 동시에 체결하는 스피드 핸들에 관한 것으로,
더욱 상세하게는 4-스크류 어댑터를 장착한 웜기어식 스피드 핸들을 이용하여 한번에 4개의 어댑터를 회전시켜 4개의 볼트를 한번에 체결할 수 있도록 하는 4-스크류 어댑터를 장착한 웜 기어식 스피드 핸들에 관한 것이다.
이러한 본 발명은 핸들(3)이 연결되며 기어식으로 설치되는 1단 회전기어(1)와,
상기 1단 회전기어(1)의 외주연에 결합되는 스크류 나사(8)가 설치되고 일측으로 볼트머리 홈(9)이 형성된 스크류 어댑터(7)와,
상기 스크류 어댑터(7)가 사방향에서 관통되는 체결용 고리(10)와 연결되는 간격유지대(11)와,
상기 간격유지대(11)의 내부에서 사방향에 열십자 형태로 연결되는 열십자 고정대(6)로 이루어져 핸들(3)의 회전으로 사방향에서 볼트를 동시에 체결할 수 있도록 함을 특징으로 하는 것이다.-
公开(公告)号：KR1020050055336A
公开(公告)日：2005-06-13
申请号：KR1020030088534
申请日：2003-12-08
Applicant: 한국항공우주연구원
IPC: F16G11/12
CPC classification number: F16G11/12
Abstract: 본 발명은 밧줄, 체인, 철사 등을 당겨서 죄는데 사용하는 죔기구인 턴버클에 관한 것이다.
본 발명에 의한 삽입홈에 나사가 형성된 삽입식 턴버클은 양단부에 암나사부를 가지는 슬리브; 상기 암나사부 중 하나에 나사 결합되는 제1 수나사부와, 상기 제1 수나사부와 연결되어 있는 제1 체결부를 포함하는 제1 로드 부재; 및 상기 암나사부 중 다른 하나에 나사 결합되는 제2 수나사부와 상기 제2 수나사부와 연결되어 있는 제2 체결부를 포함하며, 일단으로부터 길이 방향으로 상기 제1 로드 부재가 삽입될 수 있는 삽입홈이 형성되어 있고, 상기 삽입홈에 상기 제1 수나사부와 나사 결합하는 제3 암나사부가 형성되어 있는 제2 로드 부재로 이루어진다.
본 발명에 의한 삽입식 턴버클은 비슷한 규격의 기존의 턴버클보다 로드 부재의 이동 거리를 더 많이 확보하게 하며, 제1 로드 부재가 제2 로드 부재에 삽입시 양자를 나사 결합시켜 양자간에 강한 체결력을 부여하게 한다.-
公开(公告)号：KR100465878B1
公开(公告)日：2005-01-13
申请号：KR1019990067906
申请日：1999-12-31
Applicant: 한국항공우주연구원
IPC: G01N15/02
Abstract: PURPOSE: A technique for measuring spraying by using two light polarization is provided to measure a polarization ratio of scattering light beams from a liquid drop by using two color CCD cameras and two light beams of different colors having polarization perpendicular to each other, thereby measuring a size of the whole spraying in a short time at a low cost. CONSTITUTION: In a technique for measuring spraying by using two light polarization, a size of particles is measured with color CCD cameras(12,14) by using polarized dual light beams which have difference wave length from each other and are polarized perpendicularly to each other by passing through via a cylindrical lens(13) controlling a thickness and a mirror reflection plate(10) from a single sheet beam(9) generated by a cylindrical beam expander(8).
Abstract translation: 目的：通过使用两个光偏振来测量喷射的技术被提供以通过使用两个彩色CCD照相机和具有彼此偏振的不同颜色的两个光束来测量来自液滴的散射光束的偏振比，由此测量 以低成本在短时间内完成整个喷雾的大小。 组成：在使用两种偏振光测量喷雾的技术中，通过使用具有彼此不同的波长并相互垂直偏振的偏振双光束，用彩色CCD照相机（12,14）测量颗粒的尺寸 通过经由控制厚度的柱面透镜（13）和由圆柱形扩束器（8）产生的单片光束（9）的镜面反射板（10）穿过。
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公开(公告)号：KR100437523B1
公开(公告)日：2004-06-30
申请号：KR1020020015541
申请日：2002-03-22
Applicant: 한국항공우주연구원
IPC: F02C9/28
Abstract: PURPOSE: A predicting method of a steady performance of a gas turbine engine is provided to reduce the test time. CONSTITUTION: The transient effect of an engine is quantificated mathematically. The change of the fuel consumption is predicted thereby. The test data of a transient status is compensated to the test data of a steady status. Thereby, the test time, the energy consumption, the waste of manpower, the development time of the engine are reduced and the life of the developed engine is extended.
Abstract translation: 目的：提供燃气轮机稳定运行的预测方法，以缩短测试时间。 构成：发动机的瞬态效应在数学上被定量化。 由此预测燃料消耗的变化。 瞬态状态的测试数据被补偿到稳定状态的测试数据。 从而减少了测试时间，能耗，人力和开发时间，延长了发动机的使用寿命。
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公开(公告)号：KR100432133B1
公开(公告)日：2004-05-22
申请号：KR1020020015092
申请日：2002-03-20
Applicant: 한국항공우주연구원
IPC: B25J17/00
Abstract: PURPOSE: A mechanical 6-DoF(Degree of Freedom)-small cart is provided to exactly situate an object to a position of three-dimensional space, to simply transfer the object to a position desired, and enable control of the height at the installation position. CONSTITUTION: A mechanical 6-DoF(Degree of Freedom)-small cart comprises a right and left transferring device(1) transferring a lower plate(12) on body(5) right and left; a forward and backward transferring device(2) transferring an intermediate plate(23) forward and backward; a vertically transferring device(3) guiding vertical transfer of a table; and a table-turning device turning the table by gearing. In the right and left transferring device, a right and left transferring shaft(10) horizontally installed to the body transfers the lower plate right and left, passing through a right and left transferring nut protruded on the lower plate, and LM guides are connected to guide rails(13). In the forward and backward transferring device, a forward and backward transferring shaft(21), installed to the lower plate, crossed with the right and left transferring device, transfers the intermediate plate forward and backward, passing through a forward and backward transferring nut connected to the intermediate plate, and the LM guide fixed to the lower side of the intermediate plate is connected to the guide rails. The vertically transferring device rotates a vertically transferring screw installed to the intermediate plate, connected with a vertically transferring shaft forming a rack gear, and connects the vertically transferring screw to a guide shaft with a connecting unit.
Abstract translation: 目的：提供机械6-DoF（自由度）小型手推车，以便将物体精确定位到三维空间位置，将物体简单地转移到所需的位置，并且可以控制安装时的高度 位置。 组成：机械6-DoF（自由度）小型手推车包括右和左转移装置（1），左右转移主体（5）上的下板（12）; 前后移动装置（2），用于向前和向后移动中间板（23）; 垂直传送装置（3），用于引导工作台的垂直传送; 以及通过传动装置转动桌子的转台装置。 在左右转印装置中，水平安装在本体上的左右转印轴（10）左右转动下板，通过突出在下板上的右侧和左侧转印螺母，LM导向件连接到 导轨（13）。 在前后传送装置中，安装在下板上的前后传送轴（21）与左右传送装置交叉，前后传送中间板，通过连接的前后传送螺母 到中间板，并且固定到中间板下侧的LM导轨连接到导轨。 垂直传送装置使安装在中间板上的垂直传送螺杆旋转，与形成齿条的垂直传送轴连接，并通过连接单元将垂直传送螺杆连接到引导轴。
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