KR100315553B1 - Single axis thrust measurement and calibration system - Google Patents
Single axis thrust measurement and calibration system Download PDFInfo
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- KR100315553B1 KR100315553B1 KR1019990057850A KR19990057850A KR100315553B1 KR 100315553 B1 KR100315553 B1 KR 100315553B1 KR 1019990057850 A KR1019990057850 A KR 1019990057850A KR 19990057850 A KR19990057850 A KR 19990057850A KR 100315553 B1 KR100315553 B1 KR 100315553B1
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- 238000012360 testing method Methods 0.000 claims abstract description 13
- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 238000003780 insertion Methods 0.000 claims description 3
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- 238000000926 separation method Methods 0.000 claims 1
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- 239000007788 liquid Substances 0.000 abstract description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G3/00—Observing or tracking cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Abstract
본 발명은 과학 관측로켓 및 인공위성 발사용 로켓의 액체 추진기관에 있어 엔진의 추력을 정확하게 측정하는 것으로 특히 추력 측정과정에서 발생되는 저항값을 정확히 측정하여 실추력값을 구할 수 있도록 한 1축 추력 측정 및 교정장치에 관한 것이다.The present invention is to accurately measure the thrust of the engine in the liquid propulsion engine of the scientific observation rocket and the satellite launch rocket, in particular one-axis thrust measurement to obtain the actual thrust value by accurately measuring the resistance value generated during the thrust measurement process And a calibration device.
이러한 본 발명은 콘크리트벽 일측에 설치되어 교정력을 발생시키는 공압액츄에이터와, 상기 공압액츄에이터 타측에 설치되어 교정력을 측정하는 교정용로드셀과, 상기 교정용로드셀에 일측이 고정되고 콘크리트벽에 매설된 채 타측 측정용로드셀에 교정력을 전달시키는 한쌍의 교정력전달용 환봉과, 상기 교정력전달용 환봉에 연결 설치되어 전달력을 측정하는 한편 엔진연소시 발생되는 추력을 측정하는 측정용로드셀과, 상기 측정용로드셀에 엔진에서 발생되는 추력을 전달시키는 추력전달용환봉과, 상기 추력전달용 환봉을 지지하고 추력시험대 상부에 입설되는 환봉지지대와, 상기 추력전달용 환봉선단에 설치되고 엔진이 장착되는 엔진장착대와, 상기 엔진장착대에 장착된 엔진을 지지하고 추력시험대에 이동 가능케 입설되는 엔진지지대를 구비시킴으로서 이루어지는 것이다.The present invention is a pneumatic actuator installed on one side of the concrete wall to generate a calibration force, a calibration load cell installed on the other side of the pneumatic actuator to measure the calibration force, and the other side is fixed to the calibration load cell and embedded in the concrete wall A pair of calibration force transmission round bars for transmitting the calibration force to the measurement load cell, a measurement load cell connected to the calibration force transmission round bar to measure the transmission force while measuring the thrust generated during engine combustion, and to the measurement load cell A thrust transfer round bar for transmitting thrust generated from the engine, a round rod support supporting the thrust transfer round bar and installed on an upper thrust test stand, and an engine mount installed on the thrust transfer round rod end and equipped with an engine; Support the engine mounted on the engine mount and the engine support that is installed so as to move on the thrust test stand It is made by providing.
Description
본 발명은 과학 관측로켓 및 인공위성 발사용 로켓의 액체 추진기관에 있어 엔진의 추력을 정확하게 측정하는 것으로 특히 추력 측정과정에서 발생되는 저항값을 정확히 측정하여 실추력값을 구할 수 있도록 한 1축 추력 측정 및 교정장치에 관한 것이다.The present invention is to accurately measure the thrust of the engine in the liquid propulsion engine of the scientific observation rocket and the satellite launch rocket, in particular one-axis thrust measurement to obtain the actual thrust value by accurately measuring the resistance value generated during the thrust measurement process And a calibration device.
액체 로켓엔진의 발사전 지상시험에 있어서 엔진의 실제 축방향(X방향)추력을 정확하게 측정하는 것은 필수적 요소이다.Pre-launch ground testing of liquid rocket engines is essential to accurately measure the actual axial (X-direction) thrust of the engine.
이러한 추력 측정은 측정과정상에서 배관연결등에 의해 추력저항이 발생되므로 특히 이 저항값을 정확히 측정하여야만 신뢰성 있는 실추력 값을 구할 수 있게 된다.In the thrust measurement, thrust resistance is generated by the pipe connection in the measurement process, so the reliable actual thrust value can be obtained only by measuring this resistance accurately.
그러나 종래에는 상기한 바와 같이 실제 축방향 추력을 정확하게 측정할 수 있는 장치가 마련되어 있지 않아 정밀도 있는 측정이 이루어지지 못하는 것이었고 이에 따라 추력의 고정 또한 매우 신뢰성이 떨어지는 문제점이 있는 것이었다.However, in the related art, as described above, since the device for accurately measuring the actual axial thrust is not provided, the accurate measurement cannot be made, and thus, the fixing of the thrust is also very unreliable.
본 발명은 두개의 로드셀과 공압액츄에이터등을 이용하여 엔진의 축방향(X방향) 추력을 측정하고, 시스템의 저항력을 측정하여 추력을 교정할 수 있도록 하는 것이다.The present invention is to measure the axial (X direction) thrust of the engine using two load cells and pneumatic actuators, and to measure the resistance of the system to correct the thrust.
이러한 본 발명은 콘크리트벽 일측에 설치되어 교정력을 발생시키는 공압액츄에이터와, 상기 공압액츄에이터 타측에 설치되어 교정력을 측정하는 교정용로드셀과, 상기 교정용로드셀에 일측이 고정되고 콘크리트벽에 매설된 채 타측 측정용로드셀에 교정력을 전달시키는 한쌍의 교정력전달용 환봉과, 상기 교정력전달용 환봉에 연결 설치되어 전달력을 측정하는 한편 엔진연소시 발생되는 추력을 측정하는 측정용로드셀과, 상기 측정용로드셀에 엔진에서 발생되는 추력을 전달시키는 추력전달용환봉과, 상기 추력전달용 환봉을 지지하고 추력시험대 상부에 입설되는 환봉지지대와, 상기 추력전달용 환봉선단에 설치되고 엔진이 장착되는 엔진장착대와, 상기 엔진장착대에 장착된 엔진을 지지하고 추력시험대에 이동 가능케 입설되는 엔진지지대를 구비시킴으로서 이루어지는 것이다.The present invention is a pneumatic actuator installed on one side of the concrete wall to generate a calibration force, a calibration load cell installed on the other side of the pneumatic actuator to measure the calibration force, and the other side is fixed to the calibration load cell and embedded in the concrete wall A pair of calibration force transmission round bars for transmitting the calibration force to the measurement load cell, a measurement load cell connected to the calibration force transmission round bar to measure the transmission force while measuring the thrust generated during engine combustion, and to the measurement load cell A thrust transfer round bar for transmitting thrust generated from the engine, a round rod support supporting the thrust transfer round bar and installed on an upper thrust test stand, and an engine mount installed on the thrust transfer round rod end and equipped with an engine; Support the engine mounted on the engine mount and the engine support that is installed so as to move on the thrust test stand It is made by providing.
도 1 은 본 발명의 평면도1 is a plan view of the present invention
도 2 는 본 발명의 정면도2 is a front view of the present invention;
도 3 은 본 발명 환봉지지대 및 엔진지지대의 측면도Figure 3 is a side view of the present invention rod support and engine support
도 4 는 본 발명 지지수단의 일부절결 분해사시도Figure 4 is a partially exploded perspective view of the support means of the present invention
도 5 는 본 발명 지지수단의 작동상태 단면도Figure 5 is a cross-sectional view of the operating state of the support means of the present invention
[도면의 주요부분에 대한 부호의 설명][Explanation of symbols on the main parts of the drawings]
2 : 엔진 10 : 공압액츄에이터2: engine 10: pneumatic actuator
20 : 교정용로드셀 30 : 교정력전달용환봉20: load cell for calibration 30: round bar for calibration power transfer
40 : 측정용로드셀 50 : 추력전달용환봉40: load cell for measurement 50: thrust transmission round bar
60 : 엔진지지대 70 : 엔진장착대60: engine support 70: engine mount
80 : 엔진지지대 82 : 지지수단80: engine support 82: support means
82-1 : 지지체 82-2 : 이송조절볼트82-1: Support 82-2: Feed adjusting bolt
82-3 : 이송봉 82-4 : 베어링82-3: transfer rod 82-4: bearing
본 발명의 구성을 첨부된 도면에 의거 상세하게 설명하면 다음과 같다.Referring to the configuration of the present invention in detail based on the accompanying drawings as follows.
본 발명의 구성을 개략적으로 설명하면 도 1 내지 도 2 에 도시된 바와 같이 콘크리트벽(1) 일측에 설치되어 교정력을 발생시키는 공압액츄에이터(10)와,Referring to the configuration of the present invention schematically, as shown in Fig. 1 to 2 and the pneumatic actuator 10 is installed on one side of the concrete wall (1) to generate a corrective force,
상기 공압액츄에이터(10)에서 발생된 교정력을 측정하는 교정용로드셀(20)과,Calibration load cell 20 for measuring the calibration force generated in the pneumatic actuator 10,
상기 교정용로드셀(20)에 일측이 고정되고 콘크리트벽(1)에 매설된 채 타측 측정용로드셀(40)에 교정력을 전달시키는 한쌍의 교정력전달용 환봉(30)과,One pair is fixed to the orthodontic load cell 20 and a pair of orthodontic force transmission round bar 30 for transmitting the calibration force to the other measurement load cell 40 while embedded in the concrete wall (1),
상기 교정력전달용 환봉(30)에 연결 설치되어 전달력을 측정하고 엔진연소시 발생되는 추력을 측정하는 측정용로드셀(40)과,A measurement load cell 40 connected to the straight rod for straightening force transmission to measure a transmission force and a thrust generated during engine combustion;
상기 측정용로드셀(40)에 엔진(2)추력을 전달시키는 추력전달용 환봉(50)과,Thrust transmission round bar 50 for transmitting the engine (2) thrust to the load cell for measurement 40,
상기 추력전달용 환봉(50)을 지지하고 추력시험대(90)에 입설되는 환봉지지대(60)와,Round rod support 60 to support the thrust transfer ring 50 and installed in the thrust test bench 90, and
상기 추력전달용 환봉(50)선단에 설치되고 엔진(2)이 장착되는 엔진장착대(70)와,An engine mounting unit 70 installed at the tip of the thrust transmission round bar 50 and equipped with an engine 2;
상기 엔진장착대(70)에 장착된 엔진(2)을 지지하는 엔진지지대(80)로 구성됨을 알 수 있게 된다.It can be seen that it consists of an engine support 80 for supporting the engine 2 mounted on the engine mount 70.
이러한 구성으로 이루어진 본 발명을 실시 가능토록 좀 더 상세하게 설명하면 다음과 같다.When explaining the present invention made in this configuration in more detail as follows.
환봉지지대(60) 및 엔진지지대(80)는 추력시험대(90)에 입설되는 몸체(81)와,The round bar support 60 and the engine support 80 are the body 81 is installed in the thrust test bench 90, and
몸체(81)에 설치되어 환봉 및 엔진(2)을 지지하는 지지수단(82)으로 이루어지는 것으로 몸체(81)는 하부에 추력시험대(90)에 입설되는 고정대(81-1)가 형성되고 고정대(81-1)상부는 환봉 및 엔진(2)이 관통되는 개방부(81-2)를 갖는 원형체(81-3)가 설치된다.It is installed on the body 81 is composed of the support means 82 for supporting the round bar and the engine (2) is a body 81 is formed on the lower portion of the fixing stand 81-1 to be installed in the thrust test bench 90 is fixed ( 81-1) The upper portion is provided with a circular body 81-3 having a round bar and an opening portion 81-2 through which the engine 2 penetrates.
상기 원형체(81-3)에는 개방부(81-2)를 중심으로 방사상의 등간격으로 지지수단(82)이 형성된다.The support member 82 is formed in the circular member 81-3 at radial equal intervals about the opening portion 81-2.
지지수단(82)은 지지체(82-1)상부에 걸림턱(82-1-1)을 갖는 걸림홈(82-1-2)이 형성되고 양측 외벽은 원형체(81-3)에 고정되는 고정홈(82-1-3)이 형성되며 상기 걸림홈(82-1-2)에는 이송조절볼트(82-2)의 걸림돌편(82-2-1)이 끼워진 채 상부에 커버(82-3)가 씌어져 이송조절볼트(82-2)가 외부로 이탈되는 일이 없게 된다.The support means 82 has a locking groove 82-1-2 having a locking jaw 82-1-1 formed on the upper portion of the support 82-1, and both outer walls are fixed to the circular body 81-3. A groove 82-1-3 is formed, and the locking groove 82-1-2 covers the upper portion 82-3 while the locking protrusion piece 82-2-1 of the feed adjustment bolt 82-2 is fitted. ) Is covered so that the feed adjustment bolt (82-2) is not separated to the outside.
이송조절볼트(82-2)는 지지체(82-1) 삽입홈(82-1-4)에 내삽되는 이송봉(82-3)이 나사결합됨으로서 도 5 에 도시된 바와 같이 이송조절볼트(82-2)를 회전하여이송봉(82-3)을 이송시켜 환봉 및 엔진(2)의 외경이 다르더라도 지지할 수 있게 된다.The feed adjustment bolt 82-2 is a feed rod 82-3 inserted into the support 82-1 insertion groove 82-1-4 by screwing the feed adjusting bolt 82 as shown in FIG. 5. By rotating -2), the transfer rod 82-3 can be transferred to support the round rod and the engine 2 even if their outer diameters are different.
이때 도면상 도시되지 않았지만 이송봉(82-3)은 삽입홈(82-1-4)에 키 고정되므로써 이송조절볼트(82-2)와 함께 회전하지 않고 이송될 수 있게 된다.At this time, although not shown in the drawings, the feed rod 82-3 can be transported without rotation with the feed adjustment bolt 82-2 by being fixed to the insertion groove 82-1-4.
한편 이송봉(82-3)하부에는 베어링홈(82-3-1)이 형성되고 베어링홈(82-3-4)에는 추력의 원활한 전달을 위한 베어링(82-4)이 회전 가능케 고정축(82-5)으로 축설된다.On the other hand, the bearing groove (82-3-1) is formed in the lower portion of the transfer rod (82-3), and the bearing (82-4) is rotatable in the bearing groove (82-3-4) for the smooth transmission of thrust 82-5).
이때 베어링(82-4)은 이송봉(82-3)의 선단 보다 돌출되게 설치되므로써 환봉 및 엔진(2)이 베어링(82-4)의 회전력에 의해 부드럽고 원활하게 지지되고 추력(82-4)의 전달도 원활하게 된다.At this time, the bearing 82-4 is installed to protrude from the tip of the transfer rod 82-3 so that the round bar and the engine 2 are smoothly and smoothly supported by the rotational force of the bearing 82-4, and the thrust 82-4. The delivery of is also smooth.
또한 추력시험대(90)는 측정용로드셀(40)의 교체시 교체가 용이하도록 하부에 이송수단이 설치되므로써 추력시험대(90)를 이송시킨 후 측정용로드셀(40)을 교체할 수 있게 된다.In addition, the thrust test bench 90 can replace the measurement load cell 40 after transporting the thrust test bench 90 by the transfer means is installed at the bottom to facilitate the replacement of the measurement load cell 40.
이러한 구성으로 이루어진 본 발명의 작동상태를 설명하면 다음과 같다.Referring to the operating state of the present invention made of such a configuration as follows.
엔진(2)을 장착한 후 X축 방향으로 공압액츄에이터(10)를 동작시키면 교정용로드셀(20)에 그 힘(교정력)이 작용하게 된다.After the engine 2 is mounted and the pneumatic actuator 10 is operated in the X-axis direction, the force (calibration force) acts on the calibration load cell 20.
이 힘은 교정력전달용 환봉(30)을 통해 측정용로드셀(40)에도 전달되게 된다.This force is also transmitted to the measurement load cell 40 through the straight rod 30 for the correction force.
이때 엔진(2)주변의 배관, 환봉지지대(60)의 베어링(82-4)등에서 발생하는 저항력에 의해 교정용로드셀(20)과 측정용로드셀(40)의 측정값은 차이가 있게 된다.At this time, the measured values of the calibration load cell 20 and the measurement load cell 40 are different due to the resistance generated from the pipes around the engine 2 and the bearings 82-4 of the round bar support 60.
이 차이값을 후술할 연소시 추력측정값에 더해 주면 실제 엔진(2)에 의해 발생된 축방향 추력값을 얻을 수 있게 된다.By adding this difference value to the combustion thrust measurement value which will be described later, the axial thrust value generated by the actual engine 2 can be obtained.
그리고 엔진장착대(70)에 연결된 엔진의 연소시 추력은 추력전달용 환봉(50)을 통해 측정용로드셀(40)에 전달되어 측정된다.And the thrust during combustion of the engine connected to the engine mount 70 is transmitted to the load cell 40 for measurement through the thrust transfer ring 50 is measured.
상기한 추력 측정 및 교정의 순서를 요약하면 다음과 같다.A summary of the above-described thrust measurement and calibration procedures is as follows.
단계 1. 공압액츄에이터(10) 작동(비연소)Step 1. Operate the pneumatic actuator (10) (non-combustion)
추력교정값 = 교정용로드셀(20)에 의한 측정값Thrust correction value = measured value by the load cell for calibration (20)
- 측정용로드셀(40)에 의한 측정값-Measured value by the load cell 40 for measurement
단계 2. 측정용로드셀(40)에 의한 엔진(2)의 연소시 추력 측정Step 2. Measurement of thrust during combustion of the engine 2 by the measuring load cell 40
단계 3. 실제 엔진(2)의 추력 = 엔진(2)의 연소시 추력 + 추력 교정값Step 3. Actual thrust of the engine 2 = thrust during combustion of the engine 2 + thrust correction value
본 발명은 엔진의 정확한 축방향 추력측정이 가능하고 추력측정 과정에서 발생되는 저항값을 정확히 측정하므로써 추력을 고정할 수 있는 효과가 있는 것이다.The present invention is capable of accurately measuring the axial thrust of the engine and having the effect of fixing the thrust by accurately measuring the resistance value generated in the thrust measurement process.
Claims (3)
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| Application Number | Priority Date | Filing Date | Title |
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| KR1019990057850A KR100315553B1 (en) | 1999-12-15 | 1999-12-15 | Single axis thrust measurement and calibration system |
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| KR1019990057850A KR100315553B1 (en) | 1999-12-15 | 1999-12-15 | Single axis thrust measurement and calibration system |
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| KR100315553B1 true KR100315553B1 (en) | 2001-12-20 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| KR101054734B1 (en) | 2008-12-31 | 2011-08-08 | 한국항공우주연구원 | Thrust measuring device and method |
| KR101473981B1 (en) * | 2013-04-09 | 2014-12-18 | 주식회사 한화 | Thrust measurement apparatus of rocket engine, and thrust measurement method, and thrust calibration method using the same |
| KR101617388B1 (en) * | 2014-12-19 | 2016-05-02 | 한국항공우주연구원 | Thrust measurement instrument and method for aeroplane |
| KR101851074B1 (en) * | 2016-10-17 | 2018-04-20 | 주식회사 한화 | Ground fire testing device and method for thrust measurement of solid rocket motor using canted nozzle |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100445680B1 (en) * | 2001-12-12 | 2004-08-25 | 한국항공우주연구원 | Thruster Test equipment for the Cold Gas Thruster |
| KR102153603B1 (en) * | 2018-11-16 | 2020-09-08 | 정경민 | Rocket thrust measuring device |
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| US4328703A (en) * | 1980-02-14 | 1982-05-11 | Avco Corporation | Thrust measuring test stand |
| JPS57154026A (en) * | 1981-03-19 | 1982-09-22 | Ishikawajima Harima Heavy Ind Co Ltd | Thrust measuring apparatus for jet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR101054734B1 (en) | 2008-12-31 | 2011-08-08 | 한국항공우주연구원 | Thrust measuring device and method |
| KR101473981B1 (en) * | 2013-04-09 | 2014-12-18 | 주식회사 한화 | Thrust measurement apparatus of rocket engine, and thrust measurement method, and thrust calibration method using the same |
| KR101617388B1 (en) * | 2014-12-19 | 2016-05-02 | 한국항공우주연구원 | Thrust measurement instrument and method for aeroplane |
| KR101851074B1 (en) * | 2016-10-17 | 2018-04-20 | 주식회사 한화 | Ground fire testing device and method for thrust measurement of solid rocket motor using canted nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20010058424A (en) | 2001-07-06 |
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