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公开(公告)号：KR1020030054461A
公开(公告)日：2003-07-02
申请号：KR1020010084624
申请日：2001-12-26
Applicant: 한국항공우주연구원
IPC: B64G5/00
Abstract: PURPOSE: An emergency stop system of a performance test in a liquid rocket engine test equipment and a method thereof are provided to protect the test equipment and the engine by stopping promptly in an emergency with detecting pressure and vibration signals. CONSTITUTION: An emergency stop system for a liquid rocket engine test equipment is composed of a dynamic pressure sensor(1) installed in the rocket engine to measure fluctuation of high frequency dynamic pressure; an acceleration sensor(2) mounted to a rocket engine support bar to measure high frequency vibration of the structure; a high frequency measuring unit(3) supplying power to the pressure sensor and the acceleration sensor and having an amplifier sending the signal to the gauge by amplifying the signal; a high frequency pass filter(4) removing low frequency signals according to pressure and vibration signals from sensors; an analog/digital converter(5) converting signals from the high frequency pass filter; a signal deciding unit(6) deciding transmission of an emergency stop synchronous signal to a PLC(Program Logic Controller) computer(9) by detecting vibration; and a digital/analog converter(8) transmitting a TTL signal to the PLC computer in satisfying emergency condition. The rocket engine and the test equipment are protected by stopping the test quickly in an emergency.
Abstract translation: 目的：提供液体火箭发动机试验设备的性能试验的紧急停止系统及其方法，用于通过检测压力和振动信号在紧急情况下及时停止，保护试验设备和发动机。 构成：液体火箭发动机试验设备的紧急停止系统由安装在火箭发动机中的动态压力传感器（1）组成，用于测量高频动压的波动; 安装在火箭发动机支撑杆上以测量结构的高频振动的加速度传感器（2）; 向压力传感器和加速度传感器供电的高频测量单元（3），并具有通过放大信号将信号发送到量规的放大器; 高通滤波器（4）根据来自传感器的压力和振动信号去除低频信号; 模拟/数字转换器（5），转换来自高频滤波器的信号; 信号判定单元（6），通过检测振动来决定对PLC（程序逻辑控制器）计算机（9）的紧急停止同步信号的发送; 以及数字/模拟转换器（8），在满足紧急情况下向PLC计算机发送TTL信号。 火箭发动机和测试设备受到紧急停止测试的保护。
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公开(公告)号：KR100444657B1
公开(公告)日：2004-08-30
申请号：KR1020010084624
申请日：2001-12-26
Applicant: 한국항공우주연구원
IPC: B64G5/00
Abstract: PURPOSE: An emergency stop system of a performance test in a liquid rocket engine test equipment and a method thereof are provided to protect the test equipment and the engine by stopping promptly in an emergency with detecting pressure and vibration signals. CONSTITUTION: An emergency stop system for a liquid rocket engine test equipment is composed of a dynamic pressure sensor(1) installed in the rocket engine to measure fluctuation of high frequency dynamic pressure; an acceleration sensor(2) mounted to a rocket engine support bar to measure high frequency vibration of the structure; a high frequency measuring unit(3) supplying power to the pressure sensor and the acceleration sensor and having an amplifier sending the signal to the gauge by amplifying the signal; a high frequency pass filter(4) removing low frequency signals according to pressure and vibration signals from sensors; an analog/digital converter(5) converting signals from the high frequency pass filter; a signal deciding unit(6) deciding transmission of an emergency stop synchronous signal to a PLC(Program Logic Controller) computer(9) by detecting vibration; and a digital/analog converter(8) transmitting a TTL signal to the PLC computer in satisfying emergency condition. The rocket engine and the test equipment are protected by stopping the test quickly in an emergency.
Abstract translation: 目的：提供一种在液体火箭发动机测试设备中的性能测试的紧急停止系统及其方法，以在紧急情况下通过检测压力和振动信号而立即停止以保护测试设备和发动机。 一种液体火箭发动机试验设备的急停系统，包括安装在火箭发动机中的动态压力传感器（1），用于测量高频动压的波动; 安装在火箭发动机支撑杆上的加速度传感器（2），用于测量结构的高频振动; 高频测量单元（3），向压力传感器和加速度传感器供电，并且具有通过放大信号而将信号发送到量表的放大器; 高频通滤波器（4），根据来自传感器的压力和振动信号去除低频信号; 模数转换器（5），用于转换来自高频通滤波器的信号; 信号判定单元（6），通过检测振动来判定向PLC（程序逻辑控制器）计算机（9）发送紧急停止同步信号; 和一个数字/模拟转换器（8），用于在满足紧急情况下向PLC计算机发送TTL信号。 在紧急情况下，火箭发动机和测试设备受到迅速停止测试的保护。
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公开(公告)号：KR1020040051297A
公开(公告)日：2004-06-18
申请号：KR1020020079199
申请日：2002-12-12
Applicant: 한국항공우주연구원
IPC: F02K9/96
Abstract: PURPOSE: A tube bundle shaped patternator for measuring the injection form of an injector is provided to precisely measure the two-dimensional mass distribution by minimizing the sampling error factor, to smoothly drain water by avoiding the bottle-neck phenomenon, and to maintain the airtightness of a tube. CONSTITUTION: A tube bundle shaped patternator for measuring the injection form of an injector comprises a supporting panel(2) having many tube insertion holes formed vertically and connected to a fluid drain pipe(3), a sampling tube installed in the tube insertion hole independently and vertically, and a Teflon tube(6) connected to the lower portion of the sampling tube and independently connected to a sampling vessel(8) via a connecting tube(9).
Abstract translation: 目的：提供一种用于测量注射器注射形式的管束形图案，以通过最小化采样误差因子来精确测量二维质量分布，通过避免瓶颈现象来平滑排水，并保持气密性 的管子。 构成：用于测量喷射器喷射形式的管束形图案器包括一个支撑面板（2），其具有垂直形成并连接到流体排放管（3）的许多管插入孔，一个独立地安装在管插入孔中的取样管 （6），其连接到采样管的下部并且经由连接管（9）独立地连接到采样容器（8）。
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公开(公告)号：KR100495484B1
公开(公告)日：2005-06-14
申请号：KR1020020079199
申请日：2002-12-12
Applicant: 한국항공우주연구원
IPC: F02K9/96
Abstract: 본 발명은 액체로켓 엔진 개발의 초기 단계에서 수행될 연소시험 이전에 액체로켓엔진의 단일 분사기에 대한 수력학적 특성인 분무의 질량분포 자료를 획득하기 위한 비연소(수류) 시험장치로서, 수류시험 대상 단일 분사기에서 분사되는 다양한 모의 유체 조합에 대해 분사기의 하부에서 추진제의 이차원적인 질량분포를 안정적으로 계측하는 인젝터의 분무형태를 측정하는 튜브다발 형상의 패터네이터에 관한 것이다.
이러한 본 발명은 다수의 관 삽입홀(20)이 형성되고 유체 배수판(3)에 연결되는 지지판(2)과,
상기 관 삽입홀(20)에 독립되게 수직으로 설치되는 채집관(1)과,
상기 채집관(1)의 하측에 연결되며 연결판(9)을 통하여 채집용기(8)에 독립되게 연결되는 테프론 튜브(6)로 이루어짐을 특징으로 하는 것이다.
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