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公开(公告)号：KR101506395B1
公开(公告)日：2015-04-07
申请号：KR1020130106103
申请日：2013-09-04
Applicant: 한국항공우주연구원
Abstract: 노브다이얼을이용한엔진추력입력장치및 입력방법이개시된다. 화면전환단계, 엔진시동선택창의락 버튼생성단계, 락버튼을해제한후, START 버튼을눌러엔진의시동을켤 수있는엔진추력활성화단계, 지상공회전(GI)입력단계, 비행공회전(FI)입력단계, 화면전환단계를포함하여구성된다. 지상공회전(GI)입력단계혹은비행공회전(FI)입력단계는지상공회전의노브값 100 근방, 비행공회전의노브값 200근방으로숫자를올림으로써엔진추력을발생시켜, 비행공회전이하로스틱을조절하지않아도되며, 조종사가실수로잘못된값을설정할가능성이줄어추력이갑자기내려가는위험적인요인을줄일수 있으며, 입력이간편하여업무의효율성을향상시킬수 있다.
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公开(公告)号：KR101444812B1
公开(公告)日：2014-09-26
申请号：KR1020130010307
申请日：2013-01-30
Applicant: 한국항공우주연구원
Inventor： 이창호
Abstract: 본 발명은 유량계의 내부에 설치되어 유량계를 통과하는 유체에 의해 회전되되, 외주를 따라 복수 개의 블레이드가 형성되는 유량계의 회전체에 있어서,
상기 블레이드의 양측 중 유체가 유입되는 방향 측에 위치되는 일 측은 중간부가 외 측으로 돌출되도록 형성됨을 포함하고, 상기 블레이드의 상면 및 이와 대응하는 하면은 평활면인 것을 더 포함하는 것을 특징으로 한다.
본 발명에 의하면, 블레이드의 단면의 일 측 및 타 측을 타원형으로 형성시킴으로써, 유체와 블레이드 사이의 유동 박리 현상을 최소화하여 유체 유동량의 측정 정확도를 높여주는 효과가 있다.-
公开(公告)号：KR1020130033136A
公开(公告)日：2013-04-03
申请号：KR1020110097024
申请日：2011-09-26
CPC classification number: B64G1/443 , B64G1/222 , B64G2001/224 , H02S40/00
Abstract: PURPOSE: A hinge device for a satellite using a shape memory alloy and a satellite with the same are provided to minimize the deployed impact of the hinge device by removing the tradeoff between a deployment impact and rigidity after deployment. CONSTITUTION: A hinge device(30) for a satellite using a shape memory alloy comprises a first bracket(310), a second bracket(320), a tape spring hinge part(330), and a shape memory alloy cylinder fixing device(340). The first bracket is attached to one end of a satellite body by a coupling member or is attached to one end of panels if a solar cell panel is made of the multiple panels. The second bracket is attached to one end of the solar cell panel by a coupling member or is attached to one end of a panel adjacent to one end of a panel where the first bracket is attached if the solar cell panel is made of the multiple panels. The tape spring hinge part is arranged between the first and second brackets to deploy the second bracket against the first bracket. The tape spring hinge part elastically connects the first and second brackets and primarily fixes the first and second brackets after the deployment. After a shape memory alloy cylinder is deployed between the first and second brackets, the shape memory alloy cylinder fixing device secondarily fixes the first and second brackets.
Abstract translation: 目的：提供一种用于使用形状记忆合金的卫星和具有该形状记忆合金的卫星的铰链装置，以通过消除部署冲击和部署后的刚性之间的权衡来最小化铰接装置所部署的冲击。 构造：用于使用形状记忆合金的卫星的铰链装置（30）包括第一支架（310），第二支架（320），带弹簧铰链部分（330）和形状记忆合金圆筒固定装置（340） ）。 如果太阳能电池板由多个面板制成，则第一支架通过联接构件附接到卫星主体的一端或附接到面板的一端。 第二支架通过联接构件附接到太阳能电池板的一端，或者如果太阳能电池板由多个面板制成，则附接到邻近面板的一个端部的面板的一端附近的第一支架 。 带弹簧铰链部分布置在第一和第二支架之间，以将第二支架部署在第一支架上。 带弹簧铰链部分弹性地连接第一和第二支架，并且在部署之后主要固定第一和第二支架。 在形状记忆合金圆柱体部署在第一和第二托架之间之后，形状记忆合金圆筒固定装置二次固定第一和第二托架。
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公开(公告)号：KR1020100037333A
公开(公告)日：2010-04-09
申请号：KR1020080096602
申请日：2008-10-01
Applicant: 한국항공우주연구원
IPC: B64C1/12
Abstract: PURPOSE: A bushing and a bushing assembly including the same are provided to improve the adhesion of the bushing to a structure by a knurled exterior surface of the bushing. CONSTITUTION: A bushing(30) guiding the assembly and mount of different structures comprises a bushing body(31) with a coupling hole(32), and a knurled part(34) formed on in the exterior surface to guide uniform spread of an adhesive for attachment of the bushing to the structures. The pitch interval of the knurled part is 1.0 to 1.4mm.
Abstract translation: 目的：提供一种套管和包括该衬套的衬套组件，以通过衬套的滚花外表面改善衬套与结构的粘合力。 构成：引导不同结构的组件和安装件的衬套（30）包括具有联接孔（32）的衬套主体（31）和形成在外表面上的滚花部分（34），以引导粘合剂的均匀铺展 用于将衬套附接到结构。 滚花部分的间距为1.0〜1.4mm。
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公开(公告)号：KR1020040018614A
公开(公告)日：2004-03-04
申请号：KR1020020050004
申请日：2002-08-23
Applicant: 한국항공우주연구원
IPC: B64C15/00
Abstract: PURPOSE: A thrust vector control system for an aircraft is provided to improve reliability by transmitting the accurate thrust deflection angle to a controller with using a position sensor, and to control precisely and reduce take-off and landing distance by controlling the direction with rotating a propeller disk. CONSTITUTION: A thrust vector control system is composed of a rotating part(1) of the thrust vector control system connected to a motor or an engine and rotated with an internal spur gear; a fixing part(2) of the thrust vector control system connected to the rotating part by a bearing(3), composed of a pinion gear engaged with the internal spur gear and connected to the servo motor through a shaft, and fixed to the outer shell of an aircraft; and a position sensor(4) connected to the rotating part of the thrust vector control system by a position sensor motion transmission shaft(5) to indicate thrust vector.
Abstract translation: 目的：提供一种用于飞机的推力矢量控制系统，以通过使用位置传感器将精确的推力偏转角传递给控制器来提高可靠性，并通过旋转方向控制方向来精确控制并降低起飞和着陆距离 螺旋桨盘 构成：推力矢量控制系统由与马达或发动机连接的推力矢量控制系统的旋转部分（1）组成，并与内部正齿轮一起旋转; 推力矢量控制系统的固定部分（2）由轴承（3）连接到旋转部分，由与内部正齿轮啮合并通过轴连接到伺服电动机的小齿轮组成，并固定到外部 飞机外壳; 以及位置传感器（4），其通过位置传感器运动传递轴（5）连接到推力矢量控制系统的旋转部分，以指示推力矢量。
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Patent Agency Ranking
公开(公告)号：KR1020180056997A
公开(公告)日：2018-05-30
申请号：KR1020160155022
申请日：2016-11-21
Applicant: 한국항공우주연구원
CPC classification number: F16C11/12 , B64G1/222 , B64G1/443 , F16F1/027 , F16F3/02 , F16F13/00 , F16F2224/0258 , F16F7/00
Abstract: 일실시예에따른충격감쇄테이프스프링힌지는두 개이상의대상체들에각각고정되는고정부재들, 양쪽단부가상기고정부재들각각에체결되는박판형테이프스프링, 및상기테이프스프링과나란하게배치되어, 양쪽단부가상기고정부재들각각에체결되는플레이트형태의감쇄판을포함하고, 상기감쇄판과상기테이프스프링은상기고정부재들을통해이격된상기두 개이상의대상체들을연결하며, 상기감쇄판은상기테이프스프링의전개에따라발생하는전개충격을감쇄할수 있다.
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公开(公告)号：KR101634376B1
公开(公告)日：2016-06-28
申请号：KR1020140180210
申请日：2014-12-15
Applicant: 한국항공우주연구원
Inventor： 이창호
Abstract: 본발명의실시예에따른유동안정기는복수개의관통공이형성되는플레이트, 그리고각 관통공이형성된상기플레이트의내면으로부터상기각 관통공의중심을향하여돌출된날개를포함한다. 본발명에의하면, 플레이트에유체가통과할수 있는복수개의관통공이형성됨은물론, 각관통공이형성된플레이트의내면에각 관통공의중심부로돌출된복수개의날개를구비함으로써, 제한된거리내에서유체에발생된교란성분을보다신속히제거하여유량계로유입되는유체의흐름을안정화하고, 이를통해유량계의측정정확도를향상시킬수 있다.
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公开(公告)号：KR1020140097794A
公开(公告)日：2014-08-07
申请号：KR1020130010307
申请日：2013-01-30
Applicant: 한국항공우주연구원
Inventor： 이창호
Abstract: The present invention relates to a rotor of a flowmeter having a plurality of blades, while being installed inside the flowmeter and being rotated by a fluid which passes through the flowmeter. One of both sides, where the fluid flows into the blades has a central portion protruding to the outside. According to the present invention, since one or the other side of the cross section of the blades becomes elliptical, a flow separation between the fluid and blades can be minimized to increase the accuracy of the fluid flux measurement.
Abstract translation: 本发明涉及一种具有多个叶片的流量计的转子，同时安装在流量计的内部并被通过流量计的流体旋转。 流体流入叶片的两侧之一具有向外部突出的中心部分。 根据本发明，由于叶片的横截面的一侧或另一侧为椭圆形，所以可以使流体和叶片之间的流动分离最小化，从而提高流体通量测量的精度。
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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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