-
公开(公告)号：KR100447243B1
公开(公告)日：2004-09-07
申请号：KR1020020039198
申请日：2002-07-08
Applicant: 한국항공우주연구원
IPC: B64D43/00
Abstract: PURPOSE: A pressure sensor is used to measure pressure difference between both wings of an airplane, thereby measuring position angle of the wings. CONSTITUTION: More than two pressure measuring members(10) are installed in both wings of an airplane through atmosphere connection pipes(2,3). A loaded computer(4) is installed to calculate position angle with the measured pressure of the pressure measuring members.
Abstract translation: 目的：压力传感器用于测量飞机两翼之间的压力差，从而测量机翼的位置角度。 组成：两个以上的压力测量元件（10）通过大气连接管（2,3）安装在飞机的两个机翼中。 安装一个加载的计算机（4）以计算与压力测量构件的测量压力的位置角度。
-
-
公开(公告)号：KR101220698B1
公开(公告)日：2013-01-09
申请号：KR1020100123506
申请日：2010-12-06
Applicant: 한국항공우주연구원
Abstract: 별도의 저장식 냉각장치를 사용할 필요 없이 냉각 공기를 이용하여 연료를 저온으로 냉각할 수 있는 가스터빈 엔진의 고공환경 시험을 위한 냉각 장치가 개시된다. 본 발명의 일 실시예에 따른 가스터빈 엔진의 고공환경 시험을 위한 냉각 장치는 저온의 공기를 안내하는 공기 안내유닛, 상기 공기 안내유닛의 공기의 흐름상에 구비되어, 상기 저온의 공기와의 열전달을 통해 상기 수용된 연료를 냉각시키는 연료 냉각유닛, 상기 연료를 상기 연료 냉각유닛으로 공급하는 연료 공급유닛, 상기 연료 공급유닛의 일단과 상기 연료 냉각유닛을 연통하도록 형성되어 상기 연료 냉각유닛에 상기 연료를 스프레이화 하여 제공할 수 있는 스프레이 분사유닛, 그리고 상기 냉각된 연료를 배출하는 연료 배출유닛을 포함한다. 이와 같은 구성에 의하면, 연료를 스프레이화 하여 최대한 많은 표면적이 외부로 노출되도록 하여 연료의 냉각 효율을 극대화 할 수 있다.
-
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
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：KR100754013B1
公开(公告)日：2007-09-03
申请号：KR1020060109100
申请日：2006-11-06
Applicant: 한국항공우주연구원
Abstract: A swirl jet mixer is provided to improve combustion efficiency by enhancing the mixture of air and fuel in a combustion chamber by arranging the swirl jet mixer at the entrance of the combustion chamber. A swirl jet mixer consists of an inner swirl jet cylinder(200), an outer swirl jet cylinder(300), and one or more protrusions(400). The inner swirl jet cylinder has one end coupled to a fuel supply unit of a swirl generator and the other end communicated to a combustion chamber. The outer swirl jet cylinder has one end fastened to an air supply unit of the swirl generator and the other end communicated to the combustion chamber. The protrusions are formed on inner surfaces of the inner swirl jet cylinder and the outer swirl jet cylinder in a lengthwise direction.
Abstract translation: 提供旋流喷射混合器以通过在燃烧室的入口设置旋流喷射混合器来增强燃烧室中的空气和燃料的混合物来提高燃烧效率。 涡旋喷射混合器由内旋流喷射筒（200），外旋流喷射筒（300）和一个或多个突起（400）组成。 内旋流喷射缸具有一端连接到涡流发生器的燃料供应单元，另一端连通到燃烧室。 外旋流喷射缸具有一端紧固到涡流发生器的空气供应单元，另一端连通到燃烧室。 在内旋转喷射筒和外旋流喷射筒的内表面上沿长度方向形成突起。
-
Patent Agency Ranking
公开(公告)号：KR1020050063224A
公开(公告)日：2005-06-28
申请号：KR1020030094597
申请日：2003-12-22
Applicant: 한국항공우주연구원
IPC: G01C21/24
Abstract: 본 발명은 비행 제어 컴퓨터와 결합된 별 감지부와 자이로스코프를 결합한 통합 항법 시스템에 있어서, 별 영상을 촬상하여 별 영상을 검출하는 별 감지부, 비행체의 관성 정보를 검출하는 관성 센서부 및 상기 별 감지부에서 검출된 별 감지 정보로부터 상기 비행체의 자세 정보를 산출하고, 상기 관성 센서부에서 검출된 관성 정보로부터 상기 비행체의 각속도 정보를 산출하며, 상기 산출된 비행체의 자세 정보 및 각속도 정보로부터 상기 비행체의 정밀 자세를 산출하여 상기 비행 제어 컴퓨터로 전송하는 항법 컴퓨터를 포함한다.
-
公开(公告)号：KR101816052B1
公开(公告)日：2018-01-08
申请号：KR1020160132628
申请日：2016-10-13
Applicant: 한국항공우주연구원
CPC classification number: B64C39/024 , B64C29/0033 , B64C29/02 , B64C2201/021 , B64C2201/042 , B64C2201/104 , B64C2201/108 , B64C2201/162 , B64D1/00 , B64D27/24 , Y02T50/62
Abstract: 자세제어수단을구비한멀티콥터가개시되어있다. 개시된자세제어수단을구비한멀티콥터는몸체부; 상기몸체부의양쪽에지지되어추력을발생시키는다수의추력유닛; 및상기각 추력유닛을좌우및 전후로설치각도를변경하여, 상기몸체부의자세를제어하는자세제어수단;을포함하는것을특징으로한다.
-
公开(公告)号：KR1020120062300A
公开(公告)日：2012-06-14
申请号：KR1020100123506
申请日：2010-12-06
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A cooling device and cooling tube are provided to consecutively cool fuel through heat transmission with air of low temperatures because a cooling tube for cooling the fuel is exposed to the air of low temperature cooled in advance. CONSTITUTION: A cooling device for a high altitude test of a gas turbine engine comprises an air guiding unit(110), a fuel cooling unit(120), a fuel supply unit(121), spay unit(130), and a fuel discharging unit(122). The air guiding unit guides air of low temperatures. The fuel cooling unit is installed in an air flow path of the air guiding unit, thereby cooling fuel by heat transmission with the air of low temperatures. The fuel supply unit supplies the fuel to the fuel cooling unit. The spray unit connected to one end part of the fuel supply unit and fuel cooling unit sprays the fuel to the fuel cooling unit. The fuel discharging unit discharges the cooled fuel.
Abstract translation: 目的：提供一种冷却装置和冷却管，用于通过与低温空气的传热连续冷却燃料，因为用于冷却燃料的冷却管暴露于预先冷却的低温空气。 构成：用于燃气涡轮发动机的高空试验的冷却装置包括空气引导单元（110），燃料冷却单元（120），燃料供应单元（121），喷射单元（130）和排出燃料 单元（122）。 引导单元引导低温空气。 燃料冷却单元安装在空气引导单元的空气流动路径中，从而通过与低温空气的热传递来冷却燃料。 燃料供应单元将燃料供应到燃料冷却单元。 连接到燃料供应单元的一个端部的喷射单元和燃料冷却单元将燃料喷射到燃料冷却单元。 燃料排放单元排出冷却的燃料。
-
公开(公告)号：KR1020120062244A
公开(公告)日：2012-06-14
申请号：KR1020100123429
申请日：2010-12-06
Applicant: 한국항공우주연구원
CPC classification number: F01D25/30 , F01N3/025 , F02C7/20 , F02C7/26 , F05D2220/32
Abstract: PURPOSE: A variable exhaust gas ejector with a manual control, in a portion that a gas turbine engine is inserted is provided to optimize cooling efficiency by making the flow of circulation air smooth in normal operation, and to prevent fire by minimizing the backflow of fuels. CONSTITUTION: An exhaust gas ejector of a gas turbine engine comprises a duct unit(21), a variable unit(23), and a guide unit. The duct unit is connected to an exhaust gas outlet(14) of the gas turbine, and discharges exhaust gas. The duct unit is connected to the exhaust gas outlet to relatively move with respect to the exhaust gas outlet. The variable unit is made of thermal expansion materials, and connects the exhaust gas outlet and a connection part of the duct unit. The duct unit is slid in the exhaust gas outlet because the variable unit is expanded and cooled by heat. The variable unit closes a connection portion, in which the duct unit is connected to the exhaust gas outlet. The guide unit guides the sliding of the duct unit.
Abstract translation: 目的：提供一种具有手动控制的可变排气喷射器，部分燃气涡轮发动机被插入，以通过使循环空气的流动在正常运行中平滑，并通过最小化燃料回流来防止火灾，从而优化冷却效率 。 构成：燃气涡轮发动机的排气喷射器包括管道单元（21），可变单元（23）和引导单元。 管道单元连接到燃气轮机的废气出口（14）并排出废气。 管道单元连接到废气出口以相对于废气出口相对移动。 可变单元由热膨胀材料制成，并连接排气出口和管道单元的连接部分。 导管单元在废气出口中滑动，因为可变单元由热量膨胀和冷却。 可变单元关闭连接部分，其中管道单元连接到排气出口。 引导单元引导管道单元的滑动。
-
公开(公告)号：KR1020110068089A
公开(公告)日：2011-06-22
申请号：KR1020090124924
申请日：2009-12-15
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A sand and dust injection device for a piston-cylinder type gas turbine engine test is provided to test the performance of an engine in advance by injecting sand or dust of the appointed quantity artificially to an inlet of a gas turbine engine for appointed hours. CONSTITUTION: A sand and dust injection device for a piston-cylinder type gas turbine engine test includes: a sprayer(100) connected with an inlet pipeline(12) of a gas turbine engine(10) to inject high pressure air(103); and an injector(200) connected with the sprayer to supply sand and dust(30) and composed of an injection nozzle connected to the inlet pipeline and a pressure container storing high pressure air and connected with the injection nozzle to inject high pressure air through the injection nozzle.
Abstract translation: 目的：提供一种用于活塞气缸式燃气涡轮发动机试验的砂尘注射装置，用于通过将指定数量的沙尘或灰尘人工注射到燃气涡轮发动机的入口以预先指定的时间来测试发动机的性能 。 构成：用于活塞缸型燃气涡轮发动机试验的沙尘注入装置包括：与燃气涡轮发动机（10）的入口管道（12）连接以喷射高压空气（103）的喷雾器（100）; 以及喷射器（200），其与所述喷雾器连接以供应砂和灰尘（30），并且由连接到所述入口管道的喷嘴组成，以及存储高压空气并与所述喷嘴连接的压力容器，以通过所述喷射器喷射高压空气 喷嘴。
-
-
-
-
-
-
-
-
-
Search Results
33
records
(took 0.018 seconds)
