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公开(公告)号：KR101868899B1
公开(公告)日：2018-06-20
申请号：KR1020170061183
申请日：2017-05-17
Applicant: 국방과학연구소
CPC classification number: G01L15/00 , G01D1/02 , G01L19/0038
Abstract: 본발명은, 유체가흐르는관 내에설치되는몸체, 몸체의내부에형성되고, 일단에유체유입구를구비하는복수개의제1유로및 제1유로와교차되도록몸체의내부에형성되고, 제1유로와연통되며일단이압력센서기와연결되는제2유로를포함하고, 제2유로의전압력은상기제1유로를따라유입되는유체가상기제2유로에합류되어형성되는것을특징으로하는평균전압력계측프로브를개시한다. 본발명에의하면, 여러위치에서의평균전압력을단일의압력센서기를통해구할수 있으므로, 기존장치보다간편하게관내대표압력측정이가능하고, 레이크측정장치보다비용적측면에서저렴하다.
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Patent Agency Ranking
公开(公告)号：KR101268393B1
公开(公告)日：2013-05-28
申请号：KR1020130011738
申请日：2013-02-01
Applicant: 국방과학연구소
Abstract: PURPOSE: A hybrid propulsion engine is provided to supersonically discharge a subsonically combusted fuel-air using a tandem nozzle in order to lower the minimum operational Mach number of an engine to 2.0, thereby expanding the operational range of an entire dual ramjet. CONSTITUTION: A hybrid propulsion engine includes a main body(110), a complex combustor(130), a gas generator(140), and a variable flow path valve(142). The complex combustor continuously operates in a ramjet mode and in a scramjet mode. In the ramjet mode, a tandem nozzle chokes a subsonically combusted gas in the complex combustor in order to supersonically discharge the gas. In the scramjet mode, air flows in the gas generator so that the gas generator can pre-combust fuel and air which are to be combusted in the complex combustor. The variable flow path valve shuts off the gas generator in the ramjet mode. The variable flow path valve is open in the scramjet mode, and transfers the flow path of the air in order to make part of the air flowing into a hollow portion(111) flow into the gas generator. [Reference numerals] (150) Propeller control unit; (AA) Variable flow path valve opening signal; (BB) Tandem nozzle stop signal; (CC) Mach; (DD) Altitude
Abstract translation: 目的：提供一种混合动力推进发动机，以使用串联喷嘴对二次燃烧的燃料空气进行超声波排放，以将发动机的最小操作马赫数降至2.0，从而扩大整个双冲压喷气发动机的运行范围。 构成：混合动力推进发动机包括主体（110），复合燃烧器（130），气体发生器（140）和可变流路阀（142）。 复合燃烧器以冲压喷射模式和冲压喷射模式连续运行。 在冲压喷射模式中，串联喷嘴扼流在复合燃烧器中的二次燃烧气体，以便对气体进行超声波排放。 在冲压喷射模式中，空气在气体发生器中流动，使得气体发生器可以预先燃烧将在复合燃烧器中燃烧的燃料和空气。 可变流量阀在冲压喷气模式下关闭气体发生器。 可变流路阀以冲压模式打开，并且传送空气的流动路径，以使流入中空部分（111）的空气的一部分流入气体发生器。 （附图标记）（150）螺旋桨控制单元; （AA）可变流量开阀信号; （BB）串联喷嘴停止信号; （CC）马赫; （DD）海拔高度
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公开(公告)号：KR1020110082701A
公开(公告)日：2011-07-20
申请号：KR1020100002563
申请日：2010-01-12
Applicant: 국방과학연구소
Abstract: PURPOSE: A fuel injection device for reducing instable combustion, an aerial vehicle having the same, and a fuel injection control method are provided to stabilize combustion in a recirculation area and to relieve or prevent the vibration of a combustion flame. CONSTITUTION: A fuel injection device for reducing instable combustion comprises: a fuel injection unit(141) producing an air fuel mixture(151) by mixing fuel with influent air, and injecting the air fuel mixture; a flame stabilization unit(142) arranged on an injection path of the air fuel mixture to form a recirculation area of the air fuel mixture to stabilize a combustion flame of the air fuel mixture; and a secondary fuel injection unit injecting secondary fuel to the recirculation area to reduce the vibration of the combustion flame.
Abstract translation: 目的：提供一种用于减少不稳定燃烧的燃料喷射装置，具有该燃料喷射控制方法的空中飞行器和燃料喷射控制方法，以稳定再循环区域中的燃烧并减轻或防止燃烧火焰的振动。 一种用于减少不稳定燃烧的燃料喷射装置，包括：燃料喷射单元，通过将燃料与流入空气混合而产生空气燃料混合物，并喷射空气燃料混合物; 火焰稳定单元（142），布置在所述空气燃料混合物的喷射路径上，以形成所述空气燃料混合物的再循环区域，以稳定所述空气燃料混合物的燃烧火焰; 以及二次燃料喷射单元，其将二次燃料喷射到再循环区域以减少燃烧火焰的振动。
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公开(公告)号：KR101441414B1
公开(公告)日：2014-09-25
申请号：KR1020130082805
申请日：2013-07-15
Applicant: 국방과학연구소
Abstract: The present invention relates to a ground test apparatus for a variable nozzle, which can verify validity of the design and manufacturing of a variable nozzle by simulating a load state, an operating state, and a desynchronization phenomenon on the ground. The ground test apparatus for a variable nozzle, which is mounted in a jet engine and has a nozzle neck with a variable cross sectional area, can measure the degree of tilting to the central axis of the variable nozzle (10) when a synchronizing ring (12), capable of narrowing or widening flaps (10a) at the same time, operates the flaps (10a) installed along the circumference of the variable nozzle. The ground test apparatus for a variable nozzle comprises a combustion pressure simulating unit which pressurizes a variable nozzle (10) in order to simulate combustion pressure applying to the variable nozzle (10) while a jet engine operates; multiple synchronizing ring position sensing units (23) which are installed along the circumference of the variable nozzle (10) in order to sense the position of a synchronizing ring (12); and a main control unit (51) which moves the synchronizing ring (12), and stores both the combustion pressure set by the combustion pressure simulating unit and a value inputted from the combustion pressure simulating unit (23) according to a value outputted to move the synchronizing ring (12).
Abstract translation: 本发明涉及一种可变喷嘴的地面试验装置，其可以通过模拟地面上的载荷状态，操作状态和失步现象来验证可变喷嘴的设计和制造的有效性。 用于安装在喷气发动机中并且具有可变截面面积的喷嘴颈部的可变喷嘴的地面测试装置可以测量当同步环（10）的可变喷嘴（10）的中心轴线的倾斜度 同时，能够使翼片（10a）变窄或变宽的操作装置（12）操作沿着可变喷嘴的圆周安装的翼片（10a）。 可变喷嘴的地面试验装置包括燃烧压力模拟单元，其在喷气发动机运行时对可变喷嘴（10）加压，以模拟施加到可变喷嘴（10）的燃烧压力; 多个同步环位置检测单元（23），其沿着可变喷嘴（10）的圆周安装，以便感测同步环（12）的位置; 以及使所述同步环（12）移动的主控制单元（51），并且存储由所述燃烧压力模拟单元设定的燃烧压力和从所述燃烧压力模拟单元（23）输入的值，根据输出的值移动 同步环（12）。
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公开(公告)号：KR101116030B1
公开(公告)日：2012-03-13
申请号：KR1020100002563
申请日：2010-01-12
Applicant: 국방과학연구소
Abstract: 본 발명은 연료분사장치, 이를 구비하는 비행체 및 연료분사 제어방법에 관한 것으로, 상기 연료분사장치는 유입되는 공기에 연료를 혼합하여 공기연료혼합기를 생성하고 상기 공기연료혼합기를 분사하도록 형성되는 연료분사부와, 상기 공기연료혼합기의 연소 화염을 안정화시키도록 상기 공기연료혼합기의 분사 경로상에 배치되어 상기 공기연료혼합기의 재순환영역을 형성하는 화염안정화부, 및 상기 연소 화염의 진동을 저감시키도록 상기 재순환영역에 2차연료를 분사하도록 형성되는 2차연료분사부를 포함하는 연료분사장치를 제공한다. 이에 의하여 본 발명은 제트 엔진 등에서 연소 화염을 보다 안정화시키고, 연소실의 압력 진동을 저감시킨다.
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