公开(公告)号：KR1020030049797A

公开(公告)日：2003-06-25

申请号：KR1020010080114

申请日：2001-12-17

Applicant: 한국항공우주연구원

Inventor： 이수용 ,  고영성 ,  김영한

IPC: F02K9/96

Abstract: PURPOSE: Structure for testing the combustion stability of a rocket engine is provided to reduce the trials and errors accompanied with the development of an engine and to perform the combustion stability test many times in a single combustion test by efficiently inducing a pressure wave induction unit. CONSTITUTION: A pulse gun(20) has an explosion part consisting of a primer and an electricity supply unit. In a pulse gun cavity, main charge is stored. The front position is connected with a connecting bolt(2) and closed with a membrane(1). A pressure wave induction device(30) has a pulse gun pressure wave inlet portion formed in a pulse gun adapter(13) connected with the pulse gun. A nitrogen purging adapter and an engine adapter are installed in an induction cavity formed in the pressure wave induction device.

Abstract translation: 目的：提供用于测试火箭发动机燃烧稳定性的结构，以减少随发动机发展的试验和误差，并通过有效地引导压力波感应装置在单次燃烧试验中进行多次燃烧稳定性试验。 构成：脉冲枪（20）具有由底漆和电力供应单元组成的爆炸部分。 在脉冲枪腔中存储主要电荷。 前部位置与连接螺栓（2）连接并用膜（1）封闭。 压力波感应装置（30）具有形成在与脉冲枪连接的脉冲枪适配器（13）中的脉冲枪压力波入口部分。 氮气吹扫适配器和发动机适配器安装在形成在压力波感应装置中的感应腔中。

公开(公告)号：KR100424792B1

公开(公告)日：2004-03-30

申请号：KR1020010080114

申请日：2001-12-17

Applicant: 한국항공우주연구원

Inventor： 이수용 ,  고영성 ,  김영한

IPC: F02K9/96

Abstract: PURPOSE: Structure for testing the combustion stability of a rocket engine is provided to reduce the trials and errors accompanied with the development of an engine and to perform the combustion stability test many times in a single combustion test by efficiently inducing a pressure wave induction unit. CONSTITUTION: A pulse gun(20) has an explosion part consisting of a primer and an electricity supply unit. In a pulse gun cavity, main charge is stored. The front position is connected with a connecting bolt(2) and closed with a membrane(1). A pressure wave induction device(30) has a pulse gun pressure wave inlet portion formed in a pulse gun adapter(13) connected with the pulse gun. A nitrogen purging adapter and an engine adapter are installed in an induction cavity formed in the pressure wave induction device.

Abstract translation: 目的：提供用于测试火箭发动机的燃烧稳定性的结构，以减少伴随发动机开发的试验和错误，并通过有效地诱导压力波感应单元在单次燃烧测试中多次执行燃烧稳定性测试。 构成：脉冲枪（20）具有由底漆和电源单元组成的爆炸部件。 在脉冲枪腔中存储主要电荷。 前部位置连接一个连接螺栓（2）并用薄膜（1）封闭。 压力波感应装置（30）具有形成在与脉冲枪连接的脉冲枪适配器（13）中的脉冲枪压力波入口部分。 氮气净化适配器和发动机适配器安装在压力波感应装置中形成的感应腔中。

公开(公告)号：KR100315553B1

公开(公告)日：2001-12-20

申请号：KR1019990057850

申请日：1999-12-15

Applicant: 한국항공우주연구원

Inventor： 김용욱 ,  오승협 ,  김영한

IPC: B64G3/00

Abstract: 본발명은과학관측로켓및 인공위성발사용로켓의액체추진기관에있어엔진의추력을정확하게측정하는것으로특히추력측정과정에서발생되는저항값을정확히측정하여실추력값을구할수 있도록한 1축추력측정및 교정장치에관한것이다. 이러한본 발명은콘크리트벽일측에설치되어교정력을발생시키는공압액츄에이터와, 상기공압액츄에이터타측에설치되어교정력을측정하는교정용로드셀과, 상기교정용로드셀에일측이고정되고콘크리트벽에매설된채 타측측정용로드셀에교정력을전달시키는한쌍의교정력전달용환봉과, 상기교정력전달용환봉에연결설치되어전달력을측정하는한편엔진연소시발생되는추력을측정하는측정용로드셀과, 상기측정용로드셀에엔진에서발생되는추력을전달시키는추력전달용환봉과, 상기추력전달용환봉을지지하고추력시험대상부에입설되는환봉지지대와, 상기추력전달용환봉선단에설치되고엔진이장착되는엔진장착대와, 상기엔진장착대에장착된엔진을지지하고추력시험대에이동가능케입설되는엔진지지대를구비시킴으로서이루어지는것이다.

公开(公告)号：KR100408093B1

公开(公告)日：2003-12-01

申请号：KR1020000040748

申请日：2000-07-14

Applicant: 한국항공우주연구원

Inventor： 오승협 ,  박정 ,  조남경 ,  정용갑 ,  김용욱 ,  김영한 ,  강선일 ,  문일윤 ,  이재룡

IPC: G01L23/04

Abstract: PURPOSE: A method for measuring 6 components of a horizontal thrust is provided to carry out the calibration of engine mounting or a structure by obtaining calibration matrix for 6 components measured when combustion gas is discharged to the atmosphere via nozzles. CONSTITUTION: A method for measuring 6 components of a horizontal thrust includes the steps of mounting calibration load cells and measuring load cells for 6 components and obtaining a calibration constant of a thrust measuring device by applying a force to the calibration load cells and a calibration constant when an engine is mounted, carrying out calibration on the basis of the calibration constants obtained in the above step, and verifying calibration constant matrix applied in the previous step by simultaneously applying more than two calibration forces.

Abstract translation: 目的：提供一种测量水平推力的6个分量的方法，通过获得燃烧气体通过喷嘴向大气排放时测量的6个部件的校准矩阵来执行发动机安装或结构的校准。 构成：一种测量水平推力6个分量的方法包括以下步骤：安装校准称重传感器和测量6个部件的称重传感器，并通过对校准称重传感器施加力来获得推力测量设备的校准常数，以及校准常数 当安装发动机时，根据在上述步骤中获得的校准常数执行校准，并通过同时施加两个以上校准力来验证在前一步骤中应用的校准常数矩阵。

公开(公告)号：KR1020020007049A

公开(公告)日：2002-01-26

申请号：KR1020000040748

申请日：2000-07-14

Applicant: 한국항공우주연구원

Inventor： 오승협 ,  박정 ,  조남경 ,  정용갑 ,  김용욱 ,  김영한 ,  강선일 ,  문일윤 ,  이재룡

IPC: G01L23/04

Abstract: PURPOSE: A method for measuring 6 components of a horizontal thrust is provided to carry out the calibration of engine mounting or a structure by obtaining calibration matrix for 6 components measured when combustion gas is discharged to the atmosphere via nozzles. CONSTITUTION: A method for measuring 6 components of a horizontal thrust includes the steps of mounting calibration load cells and measuring load cells for 6 components and obtaining a calibration constant of a thrust measuring device by applying a force to the calibration load cells and a calibration constant when an engine is mounted, carrying out calibration on the basis of the calibration constants obtained in the above step, and verifying calibration constant matrix applied in the previous step by simultaneously applying more than two calibration forces.

Abstract translation: 目的：提供一种用于测量水平推力的6个部件的方法，用于通过获得燃烧气体通过喷嘴排放到大气中时测量的6个部件的校准矩阵来执行发动机安装或结构的校准。 构成：用于测量水平推力的6个部件的方法包括以下步骤：安装校准称重传感器并测量6个部件的称重传感器，并通过向校准称重传感器施加力并获得校准常数，并获得推力测量装置的校准常数 当安装发动机时，基于在上述步骤中获得的校准常数进行校准，并且通过同时施加两个以上的校准力来验证在前一步骤中应用的校准常数矩阵。

公开(公告)号：KR1020010058424A

公开(公告)日：2001-07-06

申请号：KR1019990057850

申请日：1999-12-15

Applicant: 한국항공우주연구원

Inventor： 김용욱 ,  오승협 ,  김영한

IPC: B64G3/00

Abstract: PURPOSE: A device for measuring and correcting a first shaft thrust is provided to detect thrust value by exactly measuring resistance value generated while measuring thrust measuring process in a liquid propulsion apparatus of an artificial satellite blastoff rocket and a science measure rocket. CONSTITUTION: A first shaft thrust measuring and correcting device comprises a pneumatic actuator(10) generating correcting force by being installed on a side of a concrete wall(1); a correcting rod cell(20) measuring the correcting force; a measuring rod cell(40) measuring the trust and transferring force; a pair of round bars(50) transferring the correcting force to the measuring rod cell by being mounted on the concrete wall; a sound bar(50) delivering thrust of an engine(2) into the measuring rod cell; a round bar supporter(60) established on a thrush testing bar(90) by supporting the thrust delivering round bar; an engine mounting plate(70) installing the engine by being mounted on a front end of the thrust delivering round bar; and an engine supporter(80). Thereby, the first shaft thrust measuring and correcting device detecting exact shaft direction thrust of the engine and equally maintains the thrust by measuring the resistance value.

Abstract translation: 目的：提供一种用于测量和校正第一轴推力的装置，通过精确测量在人造卫星爆破火箭和科学测量火箭的液体推进装置中测量推力测量过程中产生的电阻值来检测推力值。 构造：第一轴推力测量和校正装置包括气动致动器（10），其通过安装在混凝土墙（1）的侧面上产生校正力; 校正杆单元（20），其测量校正力; 测量所述信任和传递力的测量杆单元（40）; 一对圆棒（50）通过安装在混凝土墙壁上将校正力传递到测量杆单元; 将发动机（2）的推力输送到测量杆单元中的声杆（50） 通过支撑推力输送圆棒在鹅口疮试验棒（90）上建立的圆棒支撑件（60） 发动机安装板（70），其通过安装在推力传送圆杆的前端上来安装发动机; 和发动机支撑件（80）。 因此，第一轴推力测量和校正装置检测发动机的精确轴向推力，并通过测量电阻值同样保持推力。