• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.2
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• pp.73-82
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• 2020

Additively manufactured, small rocket engines are perhaps the focal activities of space startups that are developing low-cost launch vehicles. Rocket engine companies such as SpaceX and Rocket Lab in the United States, Ariane Group in Europe, and IHI in Japan have already adopted the additive manufacturing process in building key components of their rocket engines. In this paper on technology trends, an existing valve housing of a rocket engine is chosen as a case study to examine the feasibility of using additively manufactured parts for rocket engines.

• Proceedings of the IEEK Conference
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• 1998.06a
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• pp.173-176
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• 1998

The surface wave launcher from the dielectric coated coaxial cable to dielectric slab is investigated. FDTD method using local subcell and contour-path model is applied to determine the fine geometrical features. The reflection coefficient in coaxial cable region is found using extract algorithm. In this paper, two structures are presented as coaxial slot surface wave launcher. One structure has a vertical launching angle, and the other has an arbitrary launching angle. The numerical results show that a certain launching angle is minimized the reflection coefficient.

• Journal of the korean Society of Automotive Engineers
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• v.15 no.2
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• pp.84-91
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• 1993

The dynamic behaviors of a launcher under impulsive forces are analyzed. All the components of the system, ie ; chassis, turret, cage and suspension parts, are modeled as rigid. The dynamic analysis code, which is developed with the formulae describing the system equations of motion in terms of relative quantities, is used to carry out the analysis. The results show the dynamic responses of chassis and cage when the driving constraints are imposed on turret and cage.

• Proceedings of the KIPE Conference
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• 2010.11a
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• pp.215-217
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• 2010

This paper describes the test results of radiated compatibility with Ariane 5 launcher performed on the COMS Satellite test facility. Firstly, the Radiated Emission test results are analyzed in compliance with the Radiated Susceptibility requirement specification of Ariane 5 launcher. The satellite nominal operation is monitored during injection a radiated electric field corresponding to the launcher emissions levels in critical frequency ranges. And also, E-field are measured through a probe located at external units level in order to assess the EMC safety margin in Radiated mode.

• Journal of the Korea Institute of Military Science and Technology
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• v.10 no.1
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• pp.14-21
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• 2007

This paper proposes SDINS(strapdown inertial navigation system) transfer alignment method for vertical launcher using an adaptive filter in the ship. First, the velocity and attitude matching transfer alignment method is designed to align SDINS for vertical launcher. Second, the adaptive filter is employed to estimate measurement noise variance in real time using the residual of measurements. Because it is difficult to decide measurement noise variance when noise properties of the ship SDINS are changed. To verify its performance, it is compared with the EKF(Extended Kalman filter) using uncorrect measurement variance. The monte carlo simulation results show that proposed method is more effective in estimating attitude angle than EKF.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.5
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• pp.590-597
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• 2013

For a lower tier defense, the distance between a launcher and an engagement control station is quite important to estimate the proper defense area and to effectively arrange missile launchers. In this paper, we have analyzed an effectiveness of anti-ballistic missile launcher arrangement for the lower tier defense against the ballistic missile. The operation concept, specific configuration and aerodynamic characteristics of the ballistic missile such as SCUD-B/C, Nodong are considered in order to develop a realistic engagement simulation. The diverse engagement results through numerical simulations are provided to conduct the effectiveness analysis of anti-ballistic missiles.

• Proceedings of the KSME Conference
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• 2007.05a
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• pp.718-723
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• 2007

A three dimensional multibody modeling of a launcher system was developed and dynamic characteristics of the system was carried out. All the components were modeled as rigid bodies, All the components of system, ie; chassis, turret, cage and suspension parts, are modeled as rigid. The force interaction between the ground and tire was modeled as a point contact model. The factors were selected as cause and effect diagram of the MINITAB. To see effect of the stiffness, damping, mass at the launcher system, several cases of suspension parameters were compared and optimal values were selected. The stiffness and the damping coefficient were selected as design variables to minimize the required time for the next fire. The dynamic simulation was carried out using the ADAMS, and the MINITAB was employed for data analysis.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1996.11a
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• pp.1017-1022
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• 1996

This paper presents results of dynamic analysis of the missile initial motion arising from the missile detent force. Using ADAMS (Automatic Dynamic Analysis of Mechanical System) software, a non-linear 46-DOF (Degree of Freedom) model is developed for the launcher system including missile and launch tube contact problem. From the dynamic analysis, it is found that initial angular velocity of the missile increases when the missile detent force increases (more than 18 g) and also rocket exhaust plume is taken into account. To achieve the missile launching s ability, it needs to reduce the missile initial detent force and exhaust plume area of the launcher. Results of the dynamic analysis on the system natural frequency agree well with those obtained from experimental modal tests. The overall results suggest that the proposed method is a useful tool for prediction of initial missile stability as well as d :sign of the missile launcher system.

• Journal of the Korea Institute of Military Science and Technology
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• v.13 no.1
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• pp.84-90
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• 2010

Korean army currently considers the development of the new generation MLRS(Multiple Launcher Rocket System) as a new alternative, which responses on the renovation of the artillery and future battlefield environment. This study suggests that it presents cost-effectiveness of MLRS based on the Analytic Hierarchy Process and Parametric Estimating(PRICE H). According to this study, the cost-effectiveness of new generation MLRS presented that alternative A is 2.30 times and alternative B is 1.70 times, which are better than currently operating M270A1. Therefore, The best acquisition is alternative A that launcher is carried on currently operating 10ton standard truck but final acquisition alternative should be politically decided to consider viability of operator, performance and the latest of equipment.

• Journal of Electrical Engineering and Technology
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• v.13 no.5
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• pp.2067-2073
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• 2018

This paper will present the design of a novel-type velocity-controllable electromagnetic coil launcher (EMCL). By studying the influence of initial capacitor voltage on the velocity of an EMCL, the launcher voltage can be set to precisely adjust the velocity of projectile launching. The simulation of voltage and velocity in relation to time is obtained by Maxwell software. The experimental data show that for the launch accuracy to be achievable, the actual precision is 2%. Because of the excellent performance of Velocity-controllable EMCL, it can replace the air gun and applied to split Hopkinson pressure bar (SHPB).