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公开(公告)号：KR1020100025037A
公开(公告)日：2010-03-09
申请号：KR1020080083635
申请日：2008-08-27
Applicant: 한국항공우주연구원
IPC: F02C7/00
Abstract: PURPOSE: A cooled window for flame visualization is provided to enable stable flame visualization despite high temperature exposure for long time by installing a heat radiation fin for cooling in a connection part. CONSTITUTION: A visualization window is coupled with the inner circumference of a cyclic casing part(101). A combustion system connection unit(108) is formed inside a casing part. A sealing part(102) is coupled with the outside of the casing part. A cooled air inflow part(103) is formed on the outside of the casing part. A cooled air outflow part(105) is connected to the cooled air inflow part. The visualization window is interposed between the inner area of the casing part and the inner area of the sealing part.
Abstract translation: 目的：提供用于火焰可视化的冷却窗口，以便通过安装用于冷却连接部件的散热片长时间高温暴露来实现稳定的火焰可视化。 构成：可视化窗口与循环壳体部分（101）的内周耦合。 燃烧系统连接单元（108）形成在壳体部分内。 密封部分（102）与壳体部分的外部联接。 冷却空气流入部（103）形成在壳体部的外侧。 冷却空气流出部（105）与冷却空气流入部连接。 可视化窗口插入在壳体部分的内部区域和密封部分的内部区域之间。
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公开(公告)号：KR101037347B1
公开(公告)日：2011-05-26
申请号：KR1020080138384
申请日：2008-12-31
Applicant: 한국항공우주연구원
CPC classification number: G01P21/025 , G01F1/46 , G01F25/003 , G01P5/16
Abstract: 본 발명에 따르면, 항공기의 피토관과 연결되어 상기 항공기의 속도계를 점검하는 항공기 속도계 점검장치에 있어서, 내부에는 일정 크기의 공간을 갖는 삽입홈이 형성된 원통형의 부재로서, 일단부는 덮개부에 의해 밀봉되되 상기 덮개부의 일측에는 상기 삽입홈과 상기 피토관의 일측이 상호 연통되도록 구비된 분사구가 구비되며, 타단부는 개구된 형태를 갖되 상기 타단부의 내주면 둘레에는 걸림턱이 돌출되어 형성된 실린더부; 상기 실린더부의 삽입홈 내부에 삽입되어 상기 삽입홈의 내부에서 왕복 이동하도록 구비되되 상기 삽입홈의 내부 구경과 대응되는 크기 및 형태를 갖는 걸림부와, 상기 걸림부의 일측부에서 연장된 형태로 형성된 막대 형상의 손잡이부를 포함하여 구비되는 피스톤부; 및 상기 실린더부의 외부면 일측에 위치하되 투명한 재질로 형성되어, 상기 실린더부의 내부에서 왕복 이동하는 걸림부의 위치를 나타내는 표시부;를 포함하는 항공기 속도계 점검장치를 제공한다.
항공기, 피토관, 실린더, 피스톤, 공압-
公开(公告)号：KR1020100079809A
公开(公告)日：2010-07-08
申请号：KR1020080138384
申请日：2008-12-31
Applicant: 한국항공우주연구원
CPC classification number: G01P21/025 , G01F1/46 , G01F25/003 , G01P5/16
Abstract: PURPOSE: An aircraft speed meter checking device and a method thereof are provided to distinguish the malfunction and malfunction of the speed meter in early by examining the operating state of the aircraft speed meter in the normal times. CONSTITUTION: An one end of the cylinder unit(110) is sealed up with the lid unit. A nozzle is formed in one side of the lid unit in order to each other connect one side of pipe and insertion hole. A jaw is formed in circumference if it scores of the other end part of the cylinder unit. A piston unit(120) comprises a handle unit of the rod shape expanded in the one-side part of holder and holder having form and size corresponding to the inside bore of the insertion hole. A display unit(130) is located in one side of the external side of the cylinder unit. The display unit is formed into the transparent material. The display unit shows the location of the holder carried from the inside of the cylinder unit.
Abstract translation: 目的：提供一种飞机速度计检查装置及其方法，通过在正常时间检查飞机速度计的运行状态来及早区分速度计的故障和故障。 构成：气缸单元（110）的一端用盖单元密封。 在盖单元的一侧形成喷嘴，以便彼此连接管和插入孔的一侧。 如果圆柱体单元的另一端部分数十分之一，则在圆周上形成颚。 活塞单元（120）包括杆形状的把手单元，其在保持器和保持器的一侧部分中膨胀，其形状和尺寸对应于插入孔的内孔。 显示单元（130）位于气缸单元的外侧的一侧。 显示单元形成为透明材料。 显示单元显示从气缸单元的内部承载的保持器的位置。
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公开(公告)号：KR1020100061946A
公开(公告)日：2010-06-10
申请号：KR1020080120314
申请日：2008-12-01
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A fault diagnosis system for a healthy sensor of a fly-by-wire control input system is provided to enable safe flying even in case it is unable to find a normal value due to the malfunction of a displacement sensor during aviation. CONSTITUTION: A fault diagnosis system for a healthy sensor of a fly-by-wire control input system comprises a control input apparatus and a controller. The control input apparatus includes three displacement sensors. The controller comprises a flight control module which drives an actuator(4) using a signal transmitted from the control input apparatus, a voting module which extracts the most exact signal from the signals of the three displacement sensors, a detection module which detects a normal sensor in case the voting module determines the failure of two or more sensors, and a fly control module which drives the actuator according to a control input apparatus displacement sensor signal or automatic flight control algorithm.
Abstract translation: 目的：提供一种用于线控控制输入系统的健康传感器的故障诊断系统，以便在航空中由于位移传感器故障而无法找到正常值时能够安全飞行。 构成：用于线控控制输入系统的健康传感器的故障诊断系统包括控制输入装置和控制器。 控制输入装置包括三个位移传感器。 控制器包括使用从控制输入装置发送的信号驱动致动器（4）的飞行控制模块，从三个位移传感器的信号中提取最精确信号的投票模块，检测模块 在投票模块确定两个或更多个传感器的故障的情况下，以及根据控制输入装置位移传感器信号或自动飞行控制算法来驱动致动器的飞行控制模块。
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