• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.26-26
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• 1998

다련장 로켓과 같이 무유도로서 대량 발사하는 탄을 설계함에 있어서 탄의 성능을 예측하기 위해서는 사거리와 고도 해석을 통해 체계 성능을 분석하고 탄의 특성 및 외부요소의 변화 가능성을 고려하여 탄착 정확도에 대한 해석을 수행하여야 한다. 탄착 정확도는 설계하고자하는 무기체계의 신뢰성을 평가하는 최종단계이므로 매우 중요한 factor이다. 다련장 로켓과 같은 무유도 로켓의 탄착 정확도를 평가하는 가장 좋은 방법은 많은 발수의 시료를 발사하여 획득한 데이터를 바탕으로 평가하는 것이다. 그러나 이 방법은 예비 설계시에는 적용할 수 없으며 제작이 되었다 하더라도 비용이 많이 들기 때문에 적용하기 무척 어렵다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.11
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• pp.1081-1086
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• 2010

The technical procedure of an enhancement of a 120 mm rocket assisted projectile has here addressed by analyzing the ballistic performance with several the solid rocket propellants and shell designs. The performance was evaluated by aero-ballistic analyses and static ground tests of the rocket motor. Consequently, firing tests showed that one of tested models gave about 70% of extended range compared with conventional projectiles.

• Defense and Technology
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• no.8 s.270
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• pp.46-55
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• 2001

초기의 화포는 운동에너지만으로 목표물을 파괴하는 탄자를 발사하였으나, 곧 사람들은 에너지를 발산하는 화약을 그 탄자 내에 충전시키고 목표물에 충격시 폭발하도록 해서, 그 목표물을 효과적으로 파괴하는 포탄을 발명하였다. 이러한 개념은 큰 변화 없이 현재까지 지속되어서 현대 전장에서 운용하는 화포, 로켓, 미사일용 탄두와 탄약에 적용되고 있다. 또한 사람이나 경장비, 전차 등을 살상하고 파괴하기 위해 소화기탄이나 전차포용 날개안정 철갑탄처럼 운동에너지만으로 목표물을 파괴하는 탄자가 계속 사용되고 있기도 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1072-1076
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• 2017

In this paper, a numerical study has been performed to analyze flow characteristics of rocket propulsion. Through the ground spin test, combustion chamber pressure was measured. Based on the experimental results, numerical analysis was conducted under various nozzle pressure ratio conditions such as standard, operating and base pressure conditions. And it was compared with quasi-1D solution and experimental result. In addition, the difference in thrust characteristics according to the spin/non-spin of the flow conditions was confirmed at the same nozzle pressure ratio.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.213-220
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• 2014

A program that predicts trajectories of projectiles influenced by the interference flow field of helicopters is developed. The interference flow field are computed using a compressible inviscid solver in conjunction with an actuator disc model. The trajectories are predicted using 6-DOF (Degree of Freedom) equations as well as an alternative form of modified point mass equations of motion. The method for the interference flow field prediction method are validated with ROBIN(ROtor Body INteraction) model. A Sierra international bullet and a 105mm projectile are used to validate the trajectory method. Trajectories of a Sierra International bullet and a HYDRA 70 rocket firing from a helicopter are predicted.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.28 no.10
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• pp.810-818
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• 2017

This paper presents the approaching target above ground tracking based on Kalman filter applied to the proximity sensor for the active defense system. The proximity sensor located on the front of the countermeasure is not easy to detect when the anti-tank threat enters a fragment dispersion range due to limited antenna beamwidth. In addition, it is difficult for the proximity sensor to detect the anti-tank threat accurately at a terrestrial environment including various clutters. To solve these problems, this study presents the approaching target above ground tracking based on Kalman filter and applies the novel estimation method for a noise covariance matrix to improve a tracking performance. Then, a high tracking performance of Kalman filter applied the proposed noise covariance matrix is presented through field firing test results and the validity of the proposed study is examined.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.4
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• pp.52-60
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• 2015

Operation area of corps was expanded under military reformation, and extending range of 155 mm howitzer became important issue. New approach is needed to extend range to 80 kim. Ramjet engine is air breathing engine, and it can provide specific impulse several times more than solid rocket motor so that range is extended using same weight of propellant. If the ramjet engine is gun-launched system, it does not require any other booster because muzzle velocity is near Mach 3. Especially solid fuel ramjet (SFRJ) does not have any moving part so that it is favorable for gun-launching system which is under high stress during launching. In this paper, we design air intake, combustion chamber, and nozzle of 155 mm gun launched ramjet propelled artillery shell with inviscid flow assumption. We conduct parameter study to have range more than 80 km, and maximum high explosive volume.