• Journal of Mechanical Science and Technology
• /
• v.20 no.1
• /
• pp.85-93
• /
• 2006

The trend of miniaturization has been applied to the research of rockets to develop prototypes of micro rockets. In this paper, the development of a web-integrated prototyping system for three-dimensional micro rockets, and the results of combustion tests are discussed. The body of rocket was made of 6061 aluminum cylinder by lathe process. The three-dimensional micro nozzles were fabricated on the same aluminum by using micro endmills with ${\phi}100{\mu}m{sim}{\phi}500{\mu}m$ diameter. Two types of micro nozzle were fabricated and compared for performance. The total mass of the rockets was 7.32 g and that of propellant (gun powder) was 0.65 g. The thrust-to-weight ratio was between 1.58 and 1.74, and the flight test with 45 degree launch angle from the ground resulted in $46\;m{\sim}53\;m$ of horizontal flight distance. In addition, ABS housing for the micro machined rocket was fabricated using Fused Deposition Modeling (FDM). A web-based design, fabrication, and test system for micro nozzles was proposed to integrate the distributed hardware resources. Test data was sent to the designer via the same web server for the faster feedback to the rocket designer.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.22 no.1
• /
• pp.124-134
• /
• 2019

As the types of North Korea's provocation are diverse and unexpectable in the costal area, ROK navy needs to develop countermeasures, such as costal defence guided rockets. Recently ROK navy developed the PKX-B which is equipped with the new 130 mm guided rocket. The most popular rockets are LOGIR for short range targets, 130 mm guided rocket for middle range targets and Spike-NLOS for long range targets. As various guided rockets are developed, it is required to develop a guided rocket analysis model and it's analysis methodology. In addition, these guided rockets can be installed on any platforms; ground vehicle, aircraft and warship. The paper proposes systematic methodology to estimate the operational effectiveness of costal defence guided rockets. A case study exploiting the ARENA simulation model is explained to demonstrate the implementation of the proposed methodology.

• 제어로봇시스템학회:학술대회논문집
• /
• 1989.10a
• /
• pp.76-81
• /
• 1989

This paper represents the preliminary design process and the performance of the sounding rockets. At the design phase of the development, we selected rocket configuration according to results of aerodynamic weight and thrust analysis. And the payload-apogee performance of the rockets are determined with the variation of the launch angle and payload weight. Also the performance trajectory was calculated by a particle trajectory simulation. And the parameters which affect the system performance was analyzed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2004.03a
• /
• pp.550-559
• /
• 2004

Theoretical studies have been carried out to examine the influence of the grain geometry-dependent driving forces, which control the internal flow pattern of solid rockets. Numerical studies have been executed with the help of a two-dimensional code. This code solves standard k-omega turbulence equations using the coupled second order implicit unsteady formulation. It has been concluded that the grain port divergence angles have significant leverage on the formation of recirculation bubbles leading for pressure oscillations, flow separation and reattachment. In solid rockets flow reattachment will favour secondary ignition and that will add to the complexity of the starting transient prediction.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.23 no.5
• /
• pp.494-501
• /
• 2020

When we develop an OpenGL-based coastline map that displays the high resolution data of GSHHG, it takes tens of seconds until the first scene is rendered. That is because it takes time to tessellate polygons with a huge number of vertices. A commonly used solution is that it converts original data to a customized data in advance, and it displays these. But if we should use original data to display a coastline map, we need to find another solution. In this paper we suggest using a polygon splitting technique to minimize tessellation time. In order to prove its effectiveness, we implemented a software applied this technique and measured its performance. The software applied this technique took a few seconds to display the first scene and we confirmed its effectiveness.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2004.10a
• /
• pp.251-254
• /
• 2004

Hybrid rockets have many advantages over solid and liquid rockets. Hybrid rockets put forth high $I_{sp}$ like liquid rockets in spite of simple structure and low cost. As oxidizer flow rate is increased, thrust of hybrid rocket is increased accordingly. In this study, lab-scale hybrid rocket is designed, fabricated and tested. This system consists of lab-scale hybrid rocket motor, ignition system, flow system and data aquisition system. In order to control oxidizer flow rate, we construct flow rate control system by using needle valve and stepping motor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.466-475
• /
• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.3
• /
• pp.70-79
• /
• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• Journal of computational fluids engineering
• /
• v.16 no.1
• /
• pp.36-41
• /
• 2011

Numerical simulation of air-launched rockets from a helicopter was conducted to investigate the aerodynamic interference between air-launched rocket and helicopter. For this purpose, a three-dimensional inviscid flow solver has been developed based on unstructured meshes. An overset mesh technique was used to describe the relative motion between rocket and rocket launcher. The flow solver was coupled with six degree-of-freedom equation to predict the trajectory of free-flight rockets. For the validation, calculations were made for the impinging jet with inclined plate. The rotor downwash of helicopter was calculated and applied to simulation of air-launched rocket. It is shown that the rotor downwash has non-negligible effect on the air-launched rocket and its plume development.

• Advances in concrete construction
• /
• v.15 no.4
• /
• pp.229-239
• /
• 2023

Anti-tank weapons are among the infantry weapons used by the armies of many countries. Anti-tank rockets and explosives such as TNT, generally used for armour piercing, are also frequently used in terrorist attacks. These attacks damage the protection facilities built from reinforced concrete. Rockets or similar explosives' rapid speed and burst temperatures pierce reinforced concrete during strikes, resulting in casualties and damage to crucial strategic structures. This study aimed to devise an economic and applicable reinforced concrete plate that could absorb the impact of anti-tank rockets and Trinitrotoluene (TNT) type explosives. Therefore, 5 different samples, produced from C50 reinforced concrete and 150×150 cm in size, were formed by combining plates of different numbers and thicknesses. Also, a sample, which was a single thick plate, was prepared. In destructive testing, Rocket Propelled Grenade (RPG-7) was used as the anti-tank rocket launcher. As a result of this study, the impact damage was reduced with hollow concrete plate geometries, and recommendations were developed for complete prevention.