KR20040052298A - Simulator of rocket thrust generation - Google Patents
Simulator of rocket thrust generation Download PDFInfo
- Publication number
- KR20040052298A KR20040052298A KR1020020080145A KR20020080145A KR20040052298A KR 20040052298 A KR20040052298 A KR 20040052298A KR 1020020080145 A KR1020020080145 A KR 1020020080145A KR 20020080145 A KR20020080145 A KR 20020080145A KR 20040052298 A KR20040052298 A KR 20040052298A
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- South Korea
- Prior art keywords
- rocket
- thrust
- spring
- hydraulic jack
- band
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
Description
본 발명은 추력을 발생시키는 로켓 시스템의 개발시 실제 발사시험 전에 지상에서 요구되는 여러 가지 시험들을 수행하기 위하여 로켓에 추력이 발생될 때의 상황을 연출하기 위하여 실제 연소시험을 거치지 않고 지상에서 모사 추력을 발생시킬 수 있도록 하는 로켓 추력 발생 모사장치에 관한 것이다.The present invention simulates thrust on the ground without undergoing the actual combustion test to produce a situation when the thrust is generated in the rocket to perform the various tests required on the ground before the actual launch test in the development of the thrust generating rocket system. The present invention relates to a rocket thrust generation simulation device capable of generating a thrust.
로켓발사 시의 초기 상황을 연출하기 위한 종래의 방법은 실제추진기관의 연소시험에 주로 의존하였다.The conventional method for producing the initial situation at the time of rocket launch was mainly dependent on the combustion test of the actual propulsion engine.
추진기관 연소초기에 노즐에서 분출되는 화염후류로 인하여 육안으로 연소초기 상황을 관찰한다는 것은 불가능하다.It is impossible to visually observe the initial combustion situation due to the flame wake emitted from the nozzle at the early stage of the combustion engine.
또한 로켓의 발사초기의 가속도를 맞춘 추력으로 로켓을 밀어 올린다는 것은 더더욱 불가능하였다.It was even more impossible to push the rocket with thrust at the initial acceleration of the rocket's launch.
본 발명은 이러한 종래의 결점을 해소시키기 위하여 안출된 것으로 스프링을 유압잭으로 압축시키고 압축력을 로드셀을 통하여 관찰하면서 요구되는 추력을 임의로 설정할 수 있도록 하는 것이다.The present invention has been made to solve such a conventional drawback is to compress the spring with a hydraulic jack and to set the required thrust while observing the compression force through the load cell.
본 발명은 안전하게 로켓 추력 발생 상황을 모사할 수 있도록 하며, 모사 로켓의 무게에 따라 모사추력을 다르게 발생시킬 수 있도록 하는 것이다.The present invention can safely simulate the rocket thrust generation situation, it is to be able to generate a different simulation thrust according to the weight of the simulated rocket.
본 발명은 슈/레일에 올려지는 모사로켓을 고정시키는 말만 밴드와,The present invention is a horse band only to fix the woolen rocket mounted on the shoe / rail,
상기 모사로켓의 하측에서 압축판 하부에 지지되면서 추력을 모사로켓에 제공하는 스프링과,A spring that is supported by the lower compression plate at the lower side of the woolen rocket and provides a thrust to the woolen rocket,
상기 압축판 하부의 하측에 위치하며 부가되는 하중을 인디케이터를 통하여 확인하도록 하는 로드셀과,A load cell positioned below the compression plate and configured to check an added load through an indicator;
상기 로드셀의 하측에 설치되어 스프링을 압축시키는 유압잭으로 구성됨을 특징으로 하는 것이다.It is characterized in that the hydraulic jack is installed on the lower side of the load cell to compress the spring.
도 1 은 본 발명의 바람직한 실시예를 나타낸 사시도1 is a perspective view showing a preferred embodiment of the present invention
도 2 는 본 발명의 주요부분을 나타낸 사시도2 is a perspective view showing the main parts of the present invention;
도 3 은 본 발명의 주요부분을 나타낸 저면 사시도3 is a bottom perspective view showing the main parts of the present invention;
[도면의 주요 부분에 대한 부호의 설명][Description of Symbols for Main Parts of Drawing]
1 : 모사로켓 2 : 슈/레일1: woolen rocket 2: shoe / rail
3 : 말만 밴드 4 : 스프링3: horseman band 4: spring
5 : 압축판 하부 6 : 로드셀5: lower compression plate 6: load cell
7 : 유압잭7: hydraulic jack
본 발명은 임의 형태의 빔으로 형성되는 프레임의 내부 상측으로모사로켓(1)이 설치되며, 이 모사로켓(1)을 하측의 슈/레일(2)에 올려 놓고 모사로켓(1)의 하측 선단을 말만 밴드(3)를 이용하여 고정시킨다.In the present invention, a simulated rocket 1 is installed on an upper side of a frame formed of a beam of any shape, and the simulated rocket 1 is placed on a lower shoe / rail 2 and a lower end of the simulated rocket 1 is provided. Only to fix using a band (3).
상기 말만 밴드(3)는 폭발분리너트를 이용하여 양선단을 고정시켜 말만 밴드(3)를 어느 순간에 폭발력으로 분리되도록 하는 것이다.The horseman band (3) is to be fixed at both ends by using the explosion separation nut to separate the horseman band (3) at any moment by the explosive force.
말만 밴드(3)에 고정된 모사로켓(1)의 하측에는 스프링(4)을 설치하여 지지되도록 하고, 스프링(4)의 하측은 압축판 하부(5)를 통하여 지지되도록 한다.Only the lower side of the woolen rocket (1) fixed to the band (3) is installed to be supported by a spring (4), the lower side of the spring (4) is to be supported through the compression plate lower (5).
압축판 하부(5)의 하측에는 부가되는 하중을 인디케이터를 통하여 추력값을 확인할 수 있도록 로드셀(6)을 설치하고, 로드셀(6)의 하측에는 추력을 발생시키는 유압잭(7)이 설치되어 있다.The load cell 6 is provided in the lower part of the compression plate lower part 5 so that the thrust value can be confirmed through an indicator, and the hydraulic jack 7 which generate | occur | produces a thrust is provided in the lower part of the load cell 6.
이러한 구성으로 이루어진 본 발명은 유압잭(7)을 팽창시켜 발생되는 유압이 상측의 로드셀(6)에 부가되도록 한다.The present invention made of such a configuration so that the hydraulic pressure generated by expanding the hydraulic jack (7) is added to the load cell (6) of the upper side.
로드셀(6)에 부가되는 유압은 스프링(4)을 압축시키게 되며, 로드셀(6)에 부가되는 하중은 인디케이터를 통하여 확인하면서 설정하고자 하는 추력값과 일치되도록 한다.The hydraulic pressure added to the load cell 6 compresses the spring 4, and the load added to the load cell 6 is matched with the thrust value to be set while checking through the indicator.
압축되는 스프링(4)은 모사로켓(1)에 하중력을 제공하여 설정된 추력값으로 추력을 모사하는 것이다.The spring 4 to be compressed is to provide a load force to the simulated rocket 1 to simulate the thrust by the set thrust value.
이때 로켓의 추력은 아래의 식과 같다.The thrust of the rocket is as follows.
: 로켓의 추력 : Thrust of Rocket
12.15 : 스프링 상수(Kgf/mm)12.15: Spring constant (Kgf / mm)
: 스프링 압축거리 Spring compression distance
: 로켓의 질량 : Mass of rocket
상기 식에서 알 수 있는 바와 같이 설정하고자 하는 모사로켓(1)의 초기 가속도 a는 스프링 압축거리 x의 변수로 나타내어진다.As can be seen from the above equation, the initial acceleration a of the simulated rocket 1 to be set is represented by a variable of the spring compression distance x.
압축거리는 유압잭(7)을 이용하여 쉽게 조절 가능하며 스프링(4)의 압축력은 로드셀(6)을 통하여 측정되고 인디케이터를 통하여 확인할 수 있는 것이다.Compression distance is easily adjustable using the hydraulic jack (7) and the compression force of the spring (4) is measured through the load cell (6) and can be confirmed through the indicator.
스프링(4)의 압축력, 즉 추력을 설정한 후 추력모사장치와 모사로켓(1)을 묶어서 고정하고 있는 말만 밴드(3)를 연결하고 있는 폭발분리너트를 폭발시켜 분리시키면 모사로켓(1)은 초기 설정 가속도로 위로 튀어 오르듯 운동하게 된다.After setting the compression force, that is, the thrust force of the spring (4), by exploding and separating the explosion separation nut connecting the band (3) by only fixing the thrust simulator and the simulation rocket (1), the simulation rocket (1) You will be bounced up with the initial acceleration.
따라서 이 과정에서 로켓발사 초기의 현상들을 관찰하고, 지상 장비와의 간섭영역들을 확인하는 시험을 수행할 수 있다.Therefore, during this process, the phenomena of the early stage of rocket launching can be observed and a test can be performed to check the interference areas with the ground equipment.
이때, 모사로켓(1)의 무게에 따라서 유압잭(7)을 이용하여 모사추력을 다르게 발생시킬 수 있는 것이다.At this time, according to the weight of the simulation rocket (1) by using the hydraulic jack (7) will be able to generate different simulation thrust.
본 발명은 스프링을 유압잭으로 압축시키고 압축력을 로드셀을 통하여 관찰하면서 요구되는 추력을 임의로 설정할 수 있으므로 안전하게 로켓 추력 발생 상황을 모사할 수 있는 것이다.The present invention can safely set the required thrust while compressing the spring with a hydraulic jack and observing the compression force through the load cell, it is possible to safely simulate the rocket thrust generation situation.
본 발명은 로켓 발사 초기의 현상을 관찰하고 지상 장비와의 간섭영역들을확인하는 시험을 수행하여 실제 연소시험을 거치지 않고 여러 가지 시험들을 수행할 수 있는 것이다.The present invention is to observe the phenomenon of the initial stage of the rocket launch and to perform the tests to check the interference areas with the ground equipment, it is possible to perform various tests without undergoing the actual combustion test.
본 발명은 모사로켓의 무게에 따라 모사추력을 다르게 발생시켜 정확한 추력을 제공할 수 있는 것이다.The present invention can provide accurate thrust by generating different simulated thrust according to the weight of the simulated rocket.
본 발명은 시험에 소요되는 비용을 연소시험에 비하여 대폭 줄일 수 있으며, 시험 준비기간도 짧은 장점을 제공하는 것이다.The present invention can significantly reduce the cost of the test compared to the combustion test, and also provides a short test preparation period.
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KR10-2002-0080145A KR100491227B1 (en) | 2002-12-16 | 2002-12-16 | Simulator of rocket thrust generation |
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Cited By (9)
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KR20050043076A (en) * | 2003-11-05 | 2005-05-11 | 한국항공우주연구원 | Launch pad with balance for measuring rocket launcher weight |
KR100620756B1 (en) * | 2004-12-30 | 2006-09-13 | 한국항공우주연구원 | Launch Vehicle Simulation System |
CN106730829A (en) * | 2016-11-28 | 2017-05-31 | 朱雪梅 | A kind of virtual reality motor boat drive simulating equipment |
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CN109186835A (en) * | 2018-09-05 | 2019-01-11 | 北京强度环境研究所 | A kind of single-degree-of-freedom elastic spacing device for measuring force |
CN109186835B (en) * | 2018-09-05 | 2020-12-01 | 北京强度环境研究所 | Single-degree-of-freedom elastic limiting force measuring device |
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