• 한국군사과학기술학회지
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• 제15권1호
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• pp.86-92
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• 2012

When missile is launched, a launcher needs to be leveled with accuracy to avoid the systems's instability. In general, a launcher is leveled by adjusting the stroke of leveling jacks; however, it is still challenge to control the leveling jacks fast and accurately. This paper thus proposed an innovative algorithm for compensating ground inclination of a missile launcher to expand operational field of a missile launcher. Using two inclinometers attached on a launcher, a base jack for leveling is selected and the mixed gradient where launcher stands on can be estimated. Due to the limited stroke, the launcher can compensate its ground inclination within maximum stroke margin. Then, the ground inclination of a launcher can be compensated by calculated angle using weighting factors. The effectiveness of proposed algorithm is proved with a prototype missile launcher.

• 한국군사과학기술학회지
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• 제13권6호
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• pp.1147-1152
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• 2010

This paper reports a safe and environmentally-benign demilitarization method for the K305 35mm CS gas grenades launcher set(also known as E-8 launcher). The launcher system was disposed by a two-step process; complete recovery of the explosive cords and the gas grenades from the launcher followed by incineration of the recovered items in the APE-1236 Flashing Furnace. All of the 64 grenades within the 16 tubes of the E-8 launcher were safely recovered and incinerated. In this study, 32 sets of the launcher were used to make a standard operating procedure for the safe demilitarization of the launcher system and the 35mm CS cartridges were all safely destroyed in the experimental burning tests meeting the related environmental regulations.

• 한국군사과학기술학회지
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• 제11권3호
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• pp.13-18
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• 2008

During the launching phase, a launcher is vibrated by launching forces and as a result, the vibrating launcher affects the behavior of the missile. One of the important performances of the launcher is that the launched missile should be in a stable condition at the launching stage. In this paper, the launcher vibration at the launching phase is investigated in order to secure the stable flight of the missile. Using the finite element method, launching dynamics is investigated to analyze the behaviors of the launcher and missile considering the effect of the launcher vibration. In addition, performance of consecutive launching and launching dynamics of the launcher which launches missiles consecutively are studied for the various conditions after first launch.

• Journal of Magnetics
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• 제5권2호
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• pp.65-71
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• 2000

Although the electromagnetic launcher technology has been progressed significantly during the past two decades the number of firing test facilities are not many. This is prbably due to the large budget and man power required to build and maintain full scale electromagnetic launcher facilities. As the EM launcher technology's potential capabilities have been somewhat demonstrated with the full scale large systems the research is now headed more toward overcoming specific difficulties and answering questions experimentally with smaller, cost effective systems. The first half of this paper presents EM launcher's improved sub-scaling relationships based upon magnetic, thermal and momentum differential equations and EM launcher's basic equations. With the proposed scaling method the field variables can be matched or scaled linearly between the two geometrically scaled systems. The second half of the paper presents pulsed power system's circuit analysis and design technique, which is applied to the capacitor-powered small pulsed power system with crow-barring circuitry. The effect of the so-called speed volt is included. A sub-scaled small system's design is provided as an example.

• 한국생산제조학회지
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• 제24권3호
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• pp.342-347
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• 2015

The launcher pod for missiles capable of carrying a range of different warheads has been designed to be mounted on the tracked vehicle of the hybrid weapon system (HWS). In the development of this launcher pod, its structure was designed to be resilient to damage caused by shock and vibration, as well as preventing assembly errors due to the spring-back of the main composite cover and interfacing parts. This study investigated the design of the newly developed launcher pod, with its hybrid composite-metal structure, through simulation and experiment. Both simulation and actual experiments showed that the structure of the launcher is resilient to vibration and shock. The launcher pod was also subjected to vibration and shock tests to verify its performance.

• 한국추진공학회지
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• 제26권4호
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• pp.54-63
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• 2022

500 kg의 페이로드를 500 km 태양동기궤도에 이송가능한 소형발사체의 상단에 사용될 3톤급 액체로켓엔진을 설계하고 있다. 소형발사체의 1단에는 비행시험으로 검증된 75톤급 엔진을 사용한다. 상단용 엔진은 액체산소와 액체메탄을 연료로 사용되는데, 이 추진제 조합은 공통격벽탱크를 적용하여 무게 감소가 가능하고 비추력도 높다. 상단엔진의 사이클로는 저압으로 운용되어 신뢰성이 높은 팽창식 사이클을 채택했으며, 노즐 확대비 120이상에서 360초를 상회하는 비추력 성능을 보일 것으로 평가되었다. 엔진의 주요구성품인 연소기와 터보펌프는 목표 비용을 맞추기 위하여 적층제조된다. 엔진은 자가증기가압과 롤추력제어를 위하여 가열된 증기메탄을 제공하고, 이러한 기능을 가진 상단 추진기관시스템은 심우주탐사 등 다양한 임무에 확대 적용 가능할 것으로 기대된다.

• 한국군사과학기술학회지
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• 제18권3호
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• pp.316-325
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• 2015

This paper describes the design guide and its assessment process to be applied to the launcher vehicle exterior design. A launcher vehicle design is required to meet three kinds of design attributes; symbolic quality, usability, and aesthetic quality. The launcher vehicles referred to in this paper are assessed by the elements in the guidelines. A set of assessment process and methods is derived to evaluate how well the three design attributes are applied in the actual launch vehicle design. An example of assessment is shown at the last part of this paper. By this way designers can take various criteria into account integratively and select the final design. High design satisfaction and pride of the operators and the nation can be assured in the end.

• 한국군사과학기술학회지
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• 제11권6호
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• pp.21-29
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• 2008

Korean army currently considers the development of the advanced MLRS(Multiple Launcher Rocket System) as a new alternative, which responses on the renovation of the artillery and future battle field environment. Therefore, This study suggests that the development methods of MLRS based on the analysis of the future battle field environment, world wide development trends of the MLRS and operation states of the domestic MLRS. According to this study, the development methods of new generation MLRS should be included a 230/130mm combined launcher competible with conventional 227mm on the vehicle, advanced FCS(Fire Control System), GPS/INS integration navigation system, Pod of ammunitiom, ammunition carrring vehicle and guided rocket munitions, etc.

• 제어로봇시스템학회논문지
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• 제19권12호
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• pp.1111-1118
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• 2013

In this paper, the disturbance applied to launcher hatch by ship motions is introduced to identify the vertical ship motion disturbance. Basically, ship motions are comprised of 6 degrees of freedom: roll, pitch, yaw, heave, surge and sway. In the case of the shipboard launcher hatch the coupled pitch, heave and roll are significant motions to be transformed to a vertical direction motion. The maximum acceleration values are obtained from the vertical motion model and the ship motion data in accordance with ship type and hatch location on the ship. We verify that the maximum pitch motion mainly influences the launcher hatch and also present the quantity of the maximum load disturbance by the ship's motion acceleration.

• 한국추진공학회지
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• 제25권4호
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• pp.78-87
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• 2021

KSLV 상단의 임무 다각화를 위해서는 저중력 환경에서 액체 추진제의 거동을 정확히 파악하고 있어야 한다. 지상에서 저중력 환경을 모사하는 방법은 자유낙하 방법이 있지만, 공기저항이 항상 동반된다. 공기 저항을 제거하기 위하여 공기 저항 차단캡슐을 이용한 낙하 시험을 진행하였다. 공기 저항 차단캡슐 내부에 시험체를 위치하고 7 m 높이에서 1.2초 동안 낙하하여 시험체의 저중력 환경을 조성하였다. 낙하하는 동안 0.01 g 이하의 중력가속도를 측정하였으며 지표면에 도달하기 전 최소 가속도는 약 0.005 g였다. 추후 낙하 높이 및 낙하 시간이 증가한다면 개선될 수 여지가 있다.