• Journal of the Korea Institute of Military Science and Technology
• /
• v.15 no.1
• /
• pp.86-92
• /
• 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.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.13 no.6
• /
• pp.1147-1152
• /
• 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.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.11 no.3
• /
• pp.13-18
• /
• 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
• /
• v.5 no.2
• /
• pp.65-71
• /
• 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.

• Journal of the Korean Society of Manufacturing Technology Engineers
• /
• v.24 no.3
• /
• pp.342-347
• /
• 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.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.4
• /
• pp.54-63
• /
• 2022

A 3-tonf class liquid rocket engine that powers the upper stage of a small launcher and lifts 500 kg payload to 500 km SSO is designed. The small launcher is to utilize the flight-proven technology of the 75-tonf class engine for the first stage. A combination of liquid oxygen and liquid methane has been selected as their cryogenic states can provide an extra boost in specific impulse as well as enable a weight saving via the common dome arrangement. An expander cycle is chosen among others as the low-pressure operation makes it robust and reliable while a specific impulse of over 360 seconds is achievable with the nozzle extension ratio of 120. Key components such as combustion chamber and turbopump are designed for additive manufacturing to a target cost. The engine system provides an evaporated methane for the autogenous pressurization system and the reaction control of the stage. This upper stage propulsion system can be extended to various missions including deep space exploration.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.18 no.3
• /
• pp.316-325
• /
• 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.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.11 no.6
• /
• pp.21-29
• /
• 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.

• Journal of Institute of Control, Robotics and Systems
• /
• v.19 no.12
• /
• pp.1111-1118
• /
• 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.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.4
• /
• pp.78-87
• /
• 2021

Understanding the liquid propellant transport phenomena in low gravity is essential for developing Korea Space Launch Vehicle (KSLV) upper-stage for the diversity of space missions. A low-gravity environment can be simulated via the free-fall method on the ground; however, the air drag is inevitable. To reduce air resistance during free fall, air-drag shield is usually adopted. In this study, the free-fall method was performed with an air-drag shield from a 7-m height tower. The acceleration of a falling object was measured and analyzed. Low gravity below 0.01 g was achieved during 1.2-s free fall with the air-drag shield. The minimum gravitational acceleration value at 1.2-s after free fall was ±0.005 g, which is comparable to the value obtained from Bremen drop tower experiments, ±0.002 g. A prolonged free-fall duration may enhance the low-gravity quality during the drop tower experiments.