公开(公告)号：KR1020090067270A

公开(公告)日：2009-06-25

申请号：KR1020070134841

申请日：2007-12-21

Applicant: 한국항공우주연구원

Inventor： 김춘택 ,  안이기

IPC: G01M15/02 ,  G01M15/00

Abstract: A pipe connecting unit for an engine test apparatus and an engine test apparatus having the same are provided to prevent damage of pipes which connect an engine body with a facility body, thereby improving accuracy of engine thrust. A pipe connecting unit for an engine test apparatus comprises a high pressure pipe(320), a suction pipe(310), and a sealing ring(330). The high pressure pipe discharges air of predetermined pressure. The suction pipe is installed at an engine body(100). One end of the suction pipe is arranged inside the high pressure pipe. The sealing ring seals an inner circumference of the high pressure pipe and an outer circumference of the suction pipe.

Abstract translation: 用于发动机试验装置的管连接装置和具有该发动机试验装置的发动机试验装置被设置以防止将发动机体与设备体连接的管道的损坏，从而提高发动机推力的精度。 用于发动机试验装置的管连接单元包括高压管（320），吸管（310）和密封环（330）。 高压管排出预定压力的空气。 吸入管安装在发动机体（100）处。 吸入管的一端配置在高压管的内部。 密封圈密封高压管的内周和吸入管的外周。

公开(公告)号：KR100724801B1

公开(公告)日：2007-06-04

申请号：KR1020050127748

申请日：2005-12-22

Applicant: 한국항공우주연구원

Inventor： 이진근 ,  김춘택 ,  전용민 ,  이경재 ,  양수석 ,  이대성

IPC: G01M15/14 ,  G01M15/00

Abstract: A test apparatus for an intake flow in a gas turbine engine is provided to simulate various flow distortion characteristics of the air sucked into an inlet of the gas turbine engine and reduce manufacturing costs and time. A test apparatus for an intake flow in a gas turbine engine includes a front end duct, a rear end duct, and a screen frame(130). A first screen(140) and a second screen(150) are installed in the screen frame. The front end duct and the rear end duct are passages and structures for air flow. The air is sucked through the front end duct. The rear end duct is connected to a rear end of the front end duct to transmit the air to an inlet of the gas turbine engine. The front end duct is connected to the rear end duct by bolts. The screen frame is installed at a rear inner surface of the front end duct. The first screen is rotatably installed at the screen frame. The second screen is disposed at a rear surface of the first screen.

Abstract translation: 提供了一种用于燃气涡轮发动机中的进气流的测试装置，以模拟吸入燃气涡轮发动机的入口的空气的各种流动变形特性并降低制造成本和时间。 用于燃气涡轮发动机中的进气流的测试装置包括前端管道，后端管道和筛网框架（130）。 第一屏幕（140）和第二屏幕（150）安装在屏幕框架中。 前端管道和后端管道是空气流动的通道和结构。 空气通过前端管道被吸入。 后端管道连接到前端管道的后端以将空气传输到燃气涡轮发动机的入口。 前端管道通过螺栓连接到后端管道。 屏幕框架安装在前端管道的后部内表面。 第一屏幕可旋转地安装在屏幕框架上。 第二屏幕布置在第一屏幕的后表面处。

公开(公告)号：KR1020030075733A

公开(公告)日：2003-09-26

申请号：KR1020020015092

申请日：2002-03-20

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  양인영 ,  김춘택 ,  남삼식 ,  양수석 ,  이대성

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：提供一种机械式6-DoF（自由度） - 小型车，将物体精确地定位在三维空间的位置，简单地将物体转移到所需的位置，并且可以控制安装高度 位置。 构成：机械6-DoF（自由度） - 小推车包括左右转移装置（1），左右转动主体（5）上的下板（12）; 向前和向后传送中间板（23）的向前和向后传送装置（2） 引导台的垂直传送的垂直传送装置（3） 以及通过齿轮转动台子的台面转动装置。 在左右转印装置中，水平安装在主体上的左右传送轴（10）将右下左右的下板传送通过在下板上突出的左右传动螺母，LM导轨与 导轨（13）。 在向前和向后传送装置中，安装在下板上的前后传动轴（21）与左右传送装置交叉，将中间板向前和向后传递通过前后传动螺母连接 并且固定到中间板的下侧的LM导轨连接到导轨。 垂直传送装置使安装到中间板的垂直传送螺杆旋转，与形成齿条的竖直传送轴连接，并将垂直传送螺杆连接到具有连接单元的引导轴。

公开(公告)号：KR101302078B1

公开(公告)日：2013-09-05

申请号：KR1020110140984

申请日：2011-12-23

Applicant: 한국항공우주연구원

Inventor： 이보화 ,  김춘택 ,  박부민

IPC: H02J7/34 ,  H02J7/35

Abstract: 본 발명은 하이브리드 전력원용 액티브 전력제어 시스템 및 그 방법에 관한 것으로서, 상술한 목적을 달성하기 위한 본 발명에 하이브리드 전력원용 액티브 전력제어 시스템은 따른 태양에너지를 전기에너지로 변환하여 비행체의 추진에 필요한 전력을 출력하는 태양전지, 화학적에너지를 전기에너지로 변환하여 비행체의 추진에 필요한 전력을 출력하는 연료전지, 태양전지와 연료전지에서 출력된 전력을 저장하여 필요한 경우 출력하는 배터리, 및 태양전지와 연료전지 그리고 배터리를 제어하여 출력되는 전력을 비행체에 공급하도록 관리하는 전력관리 모듈를 포함하여, 추진시스템의 안정성을 확보하고, 각 전력원의 전력을 효율적으로 사용할 수 있도록 한다.

公开(公告)号：KR1020030076839A

公开(公告)日：2003-09-29

申请号：KR1020020015541

申请日：2002-03-22

Applicant: 한국항공우주연구원

Inventor： 양인영 ,  전용민 ,  김춘택 ,  양수석 ,  이대성

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：提供燃气轮机发动机稳定性能的预测方法，以减少测试时间。 构成：发动机的瞬态效应在数学上被量化。 从而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。 因此，测试时间，能源消耗，人力浪费，发动机开发时间减少，发动机发动机寿命延长。

公开(公告)号：KR1020030074001A

公开(公告)日：2003-09-19

申请号：KR1020020014205

申请日：2002-03-15

Applicant: 한국항공우주연구원

Inventor： 전용민 ,  양인영 ,  김춘택 ,  남삼식 ,  양수석 ,  이대성

IPC: F16B35/06

CPC classification number: F16B35/06

Abstract: PURPOSE: An eye bolt having a semicircular head section is provided to prevent the eye bolt from being broken or damaged due to vertical and horizontal loads applied thereto by forming the semicircular head section at an upper portion of the eye bolt. CONSTITUTION: An eye bolt(1) includes a semicircular head section(2) having a semicircular space section(3) therein. A lower planar head section(4) is formed at a lower portion of the semicircular head section(2) so as to horizontally make contact with an object. A screw section(5) is protruded from the lower planar head section(4). The lower planar head section(4) has a length longer than a diameter of the screw section(5) more than three times. At least one screw hole is formed in the object so as to receive the screw section(5) therein.

Abstract translation: 目的：提供具有半圆形头部的眼睛螺栓，以通过在眼螺栓的上部形成半圆形头部来防止眼螺栓由于施加于其上的垂直和水平负载而破损或损坏。 构成：眼睛螺栓（1）包括在其中具有半圆形空间部分（3）的半圆形头部（2）。 下平面头部（4）形成在半圆头部（2）的下部，从而水平地与物体接触。 螺钉部（5）从下平面头部（4）突出。 下平面头部部分（4）的长度大于螺杆部分（5）的直径大于三倍。 在物体中形成至少一个螺纹孔，以便在其中容纳螺钉部分（5）。