KR20050043076A - Launch pad with balance for measuring rocket launcher weight - Google Patents

Launch pad with balance for measuring rocket launcher weight Download PDF

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Publication number
KR20050043076A
KR20050043076A KR1020030077841A KR20030077841A KR20050043076A KR 20050043076 A KR20050043076 A KR 20050043076A KR 1020030077841 A KR1020030077841 A KR 1020030077841A KR 20030077841 A KR20030077841 A KR 20030077841A KR 20050043076 A KR20050043076 A KR 20050043076A
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South Korea
Prior art keywords
weight
launch pad
rocket projectile
projectile
propellant
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KR1020030077841A
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Korean (ko)
Inventor
하성업
이중엽
정태규
한상엽
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한국항공우주연구원
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Priority to KR1020030077841A priority Critical patent/KR20050043076A/en
Publication of KR20050043076A publication Critical patent/KR20050043076A/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01G—WEIGHING
    • G01G3/00—Weighing apparatus characterised by the use of elastically-deformable members, e.g. spring balances
    • G01G3/12—Weighing apparatus characterised by the use of elastically-deformable members, e.g. spring balances wherein the weighing element is in the form of a solid body stressed by pressure or tension during weighing
    • G01G3/14—Weighing apparatus characterised by the use of elastically-deformable members, e.g. spring balances wherein the weighing element is in the form of a solid body stressed by pressure or tension during weighing measuring variations of electrical resistance

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

본 발명은 발사대에 장착되는 로켓 발사체의 무게측정을 위한 저울이 장착된 발사대의 구조 및 형태에 관한 것으로, 더욱 상세하게는 발사대에 로켓 발사체의 무게를 측정할 수 있는 로드셀 형의 저울을 장착하여 발사체의 추진체 충전전과 충전 후의 무게를 정확히 판단할 수 있도록 하는 로켓 발사체 무게 측정을 위한 저울이 장착된 발사대에 관한 것이다.The present invention relates to a structure and form of a launch pad equipped with a scale for weighing a rocket projectile mounted on a launch pad, and more particularly, to a launch cell equipped with a load cell scale capable of measuring the weight of a rocket projectile on a launch pad. This invention relates to a launch pad equipped with a scale for weighing a rocket projectile that allows to accurately determine the weight of the propellant before and after charging.

이러한 본 발명은 발사대(3)의 화염 방출구(2) 주변으로 로켓 발사체(4)의 무게측정을 할 수 있는 로드셀(load cell)형의 저울(1)을 장착하여, 발사체의 추진제 충전 전 무게와 후 무게를 정확히 판단할 수 있도록 하는 것이다.The present invention is equipped with a load cell-type scale (1) capable of measuring the weight of the rocket projectile (4) around the flame outlet (2) of the launch pad (3), the weight before the propellant charge of the projectile It is to be able to accurately determine the weight after.

Description

로켓 발사체 무게 측정을 위한 저울이 장착된 발사대{Launch Pad with Balance for Measuring Rocket Launcher Weight}Launch Pad with Balance for Measuring Rocket Launcher Weight}

본 발명은 발사대에 장착되는 로켓 발사체의 무게측정을 위한 저울이 장착된 발사대의 구조 및 형태에 관한 것으로, 더욱 상세하게는 발사대에 로켓 발사체의 무게를 측정할 수 있는 로드셀 형의 저울을 장착하여 발사체의 추진체 충전전과 충전 후의 무게를 정확히 판단할 수 있도록 하는 로켓 발사체 무게 측정을 위한 저울이 장착된 발사대에 관한 것이다.The present invention relates to a structure and form of a launch pad equipped with a scale for weighing a rocket projectile mounted on a launch pad, and more particularly, to a launch cell equipped with a load cell scale capable of measuring the weight of a rocket projectile on a launch pad. This invention relates to a launch pad equipped with a scale for weighing a rocket projectile that allows to accurately determine the weight of the propellant before and after charging.

액체 추진제를 충전하여 발사대에 장착되는 로켓 발사체의 무게를 측정하는 데, 추진제 충전무게는 다음과 같은 중요한 의미를 지닌다.Filling the liquid propellant to measure the weight of the rocket projectile mounted on the launch pad, the propellant weight has the following important meanings.

첫째, 단위시간당 엔진으로 공급되는 추진제의 무게는 추력 등의 엔진의 성능을 나타내는 중요한 변수를 갖는다.First, the weight of propellant supplied to the engine per unit time has an important variable indicating the engine performance such as thrust.

둘째, 발사체 추진기관 시스템이 생성할 수 있는 총역적(total impulse)은 충전된 전체 추진제 무게에 크게 의존하게 된다.Second, the total impulse that a projectile propulsion system can produce is highly dependent on the total weight of the propellant charged.

셋째, 발사 직후의 비행 안정화에 중요한 척도인 발사체 초기 가속도는 발사체의 초기 무게와 밀접한 관련을 갖는다.Third, projectile initial acceleration, an important measure for flight stabilization immediately after launch, is closely related to the initial weight of the projectile.

넷째, 추진제 충전 전후의 발사체 무게비, 즉 구조비는 전체 비행궤적 평가 및 임무수행에 있어 중요한 변수가 된다.Fourth, the projectile weight ratio, that is, rescue ratio, before and after propellant charge becomes an important variable in the overall flight trajectory evaluation and mission performance.

이에 통상적으로 액체추진제 로켓 발사체의 경우 추진제를 충전하기전 무게는 통상 조립자에서 측정이 되어지며, 발사대로 운송이 되어 장착된 후에는 유체 상태의 추진제가 공급됨에 따라 추진제 공급무게를 지상공급장치의 유량계와 발사체의 추진제 탱크 레벨 센서 등을 통하여 계산하게 된다.In the case of a liquid propellant rocket projectile, the weight before charging the propellant is usually measured at the assembler, and after the transport is mounted on the launch pad, the propellant weight is supplied as the fluid propellant is supplied. Calculations are made through flowmeters and propellant tank level sensors of the projectile.

그러나 이러한 무게 예측방법은 다음과 같이 여러 가지의 문제점을 가지게 된다.However, this weight prediction method has various problems as follows.

첫째, 추진제 유량계와 레벨 센서의 이용은 간접측정법으로서 온도, 압력에 대한 밀도를 이용하여 계산되어짐에 따라 온도, 압력 등의 주변 변화에 따른 계측 오차를 유발할 수 있다.First, the use of a propellant flow meter and a level sensor may cause measurement errors due to ambient changes such as temperature and pressure as it is calculated using density for temperature and pressure as an indirect measurement method.

둘째, 유량계와 레벨 센서는 타 센서에 비해 오차가 큰 편으로 상대적으로 낮은 측정신뢰도를 나타내게 된다.Second, the flowmeter and the level sensor have a relatively large error compared to other sensors, resulting in a relatively low measurement reliability.

셋째, 케로신 등과 같이 순물질이 아닌 추진제 사용의 경우 정확한 물성관리, 특히 밀도관리가 힘들다.Third, in the case of the use of propellants other than pure substances such as kerosene, accurate physical property management, especially density management, is difficult.

넷째, 극저온 추진제의 경우 안정화를 위하여 기화된 추진제를 방출함에 따라 충전된 추진제의 온도가 변화하여 추진제의 밀도가 변화함은 물론 기화되어 배출된 추진제 량을 정확히 측정할 수 없는 등의 이유로 발사 직전의 정확한 발사체 무게를 아는 것은 매우 어려운 일이다.Fourth, in case of cryogenic propellant, the temperature of charged propellant is changed by releasing evaporated propellant for stabilization, the density of propellant is changed, and the amount of propellant discharged from vaporization cannot be measured accurately. Knowing the exact projectile weight is very difficult.

본 발명은 이러한 종래의 결점을 해소시키기 위하여 안출된 것으로, 발사대에 로켓 발사체의 무게 측정을 할 수 있는 로드셀형의 저울을 장착하여 발사체의 추진제 충전 전 무게와 충전 후 무게를 정확히 판단할 수 있도록 하는 것이다.The present invention has been made to solve the above-mentioned drawbacks, it is equipped with a load cell scale that can measure the weight of the rocket projectile on the launch pad to accurately determine the weight before and after the propellant charge of the projectile. will be.

본 발명은 단순하고 직접적인 측정을 통하여 높은 신뢰도의 발사체 무게 자료를 제공하여 임무 수행의 정확한 판단을 내릴 수 있도록 하는 것이다.The present invention provides a highly reliable projectile weight data through a simple and direct measurement to make an accurate determination of mission performance.

본 발명은 수평방향으로 설치되는 발사대(3)의 저면으로 적어도 4방향에 철구조물(5)을 설치하여 지상에서 일정한 높이에 발사대(3)가 설치되도록 하는 것이다.The present invention is to install the steel structure (5) in at least four directions to the bottom surface of the launch pad (3) installed in the horizontal direction so that the launch pad (3) is installed at a constant height from the ground.

상기 발사대(3)에는 화염 방출구(2)를 설치하여 로켓 발사체(4)가 직립되게 형성되어 발사 가능하도록 설치한다.The launch pad 3 is provided with a flame outlet 2 so that the rocket projectile 4 is formed to be upright and can be installed.

상기 로켓 발사체(4)의 후류 화염 방출구(2)가 위치하는 발사대(3)에 3개 또는 4개의 로드셀형 저울(1)을 분산 배치시키거나 등간격으로 설치하되, 발사대(3)에 설치되어 상측으로 로켓 발사체(4)가 장착되도록 하여 로켓 발사체(4)의 무게를 측정할 수 있도록 구성하는 것이다.Distribute three or four load cell scales 1 on the launch pad 3 in which the wake flame outlet 2 of the rocket projectile 4 is located or at equal intervals, but install on the launch pad 3. The rocket projectile 4 is mounted upward so that the weight of the rocket projectile 4 can be measured.

이러한 구성으로 이루어진 본 발명은 발사대(3)에 설치된 화염 방출구(2)의 주변으로 로드셀형 저울(1)을 설치하여 로켓 발사체(4)의 무게를 측정할 수 있는 것이다.According to the present invention having the above configuration, the load cell scale 1 may be installed around the flame discharge port 2 installed in the launch pad 3 to measure the weight of the rocket projectile 4.

또한 로켓 발사체(4)에 액체 추진제의 충전 전 또는 후의 무게를 직접 측정할 수 있도록 하여 충전된 추진제 무게를 정확하게 파악할 수 있도록 하는 것이다.In addition, it is possible to directly determine the weight of the rocket projectile 4 before or after the filling of the liquid propellant to accurately determine the weight of the charged propellant.

그리고 액체 추진제의 충전전 또는 후의 무게를 측정하여 충전된 추진제의 무게를 통하여 정확한 성능평가 및 임무 수행을 가능케 하는 것이다.In addition, by measuring the weight of the liquid propellant before or after charging, it is possible to perform accurate performance evaluation and mission through the weight of the charged propellant.

본 발명은 로켓 발사체의 무게 측정을 할 수 있는 로드셀형 저울이 장착된 발사대에 로켓 발사체를 설치하여, 액체 추진제의 충전 전, 후의 발사체 무게를 단순하고 직접적인 측정을 통하여 정확히 판단할 수 있도록 하고, 이러한 무게 자료를 제공하여 임무 수행의 정확한 판단을 내릴 수 있도록 하는 것이다.The present invention installs a rocket projectile on a launch pad equipped with a load cell scale capable of measuring the weight of the rocket projectile, so that the projectile weight before and after the filling of the liquid propellant can be accurately determined through a simple and direct measurement. It provides weight data so that you can make an accurate determination of mission performance.

도 1 은 본 발명의 실시예를 나타낸 설치상태도1 is an installation state showing an embodiment of the present invention

도 2 는 본 발명중 발사대에 대한 평면도2 is a plan view of the launch pad according to the present invention;

[도면의 주요 부분에 대한 부호의 설명][Description of Symbols for Main Parts of Drawing]

1 : 로드셀형 저울 2 : 화염 방출구1: Load cell scale 2: Flame discharge port

3 : 발사대 4 : 로켓 발사체3: launch pad 4: rocket projectile

Claims (3)

발사대(3)에 로켓 발사체(4)를 설치하여 로켓 발사체의 무게를 측정하는 구조에 있어서,In the structure of measuring the weight of the rocket projectile by installing the rocket projectile (4) on the launch pad (3), 상기 발사대(3)의 화염 방출구(2)의 주변에 로드셀형 저울(1)을 분산배치시켜 로켓 발사체(4)에 액체 추진제의 충전 전, 후 무게를 측정하도록 함을 특징으로 하는 로켓 발사체 무게 측정을 위한 저울이 장착된 발사대.Distributing the load cell scale (1) around the flame outlet (2) of the launch pad (3) so as to measure the weight before and after the filling of the liquid propellant to the rocket projectile (4) Launch pad with balance for measurement. 제1항에 있어서, 로드셀형 저울(1)은 화염 방출구(2)의 주변에 3개 또는 4개를 설치함을 특징으로 하는 로켓 발사체 무게 측정을 위한 저울이 장착된 발사대.2. Launch pad equipped with a scale for weighing a rocket projectile according to claim 1, characterized in that three or four load cell scales (1) are installed around the flame outlet (2). 제1항에 있어서, 로드셀형 저울(1) 위에 로켓 발사체(4)를 위치시킴을 특징으로 하는 로켓 발사체의 무게 측정을 위한 저울이 장착된 발사대.2. A launch pad according to claim 1, characterized in that the rocket projectile (4) is positioned on the load cell scale (1).
KR1020030077841A 2003-11-05 2003-11-05 Launch pad with balance for measuring rocket launcher weight KR20050043076A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100911687B1 (en) * 2007-09-07 2009-08-10 한국항공우주연구원 Methode for setting?reference filling level of propellant
KR101235033B1 (en) * 2010-12-30 2013-02-21 국방과학연구소 Method of additional thrust modeling and method of performance varification using the same

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06331469A (en) * 1993-05-06 1994-12-02 Proel Technol Spa Equipment and method for measuring thrust of propulsion device used in space on ground
KR20040009474A (en) * 2002-07-23 2004-01-31 현대모비스 주식회사 injection uniformity automatic measurement unit and method of injector for rocket engine
KR20040052298A (en) * 2002-12-16 2004-06-23 한국항공우주연구원 Simulator of rocket thrust generation
KR100445680B1 (en) * 2001-12-12 2004-08-25 한국항공우주연구원 Thruster Test equipment for the Cold Gas Thruster

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06331469A (en) * 1993-05-06 1994-12-02 Proel Technol Spa Equipment and method for measuring thrust of propulsion device used in space on ground
KR100445680B1 (en) * 2001-12-12 2004-08-25 한국항공우주연구원 Thruster Test equipment for the Cold Gas Thruster
KR20040009474A (en) * 2002-07-23 2004-01-31 현대모비스 주식회사 injection uniformity automatic measurement unit and method of injector for rocket engine
KR20040052298A (en) * 2002-12-16 2004-06-23 한국항공우주연구원 Simulator of rocket thrust generation

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100911687B1 (en) * 2007-09-07 2009-08-10 한국항공우주연구원 Methode for setting?reference filling level of propellant
KR101235033B1 (en) * 2010-12-30 2013-02-21 국방과학연구소 Method of additional thrust modeling and method of performance varification using the same

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