• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.49-59
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• 2008

In this study, the design method of a 155 mm Solid Fuel Ramjet projectile is proposed and a flight performance analysis program through mathematical modelling is developed. Through flight performance analysis, ramjet performance during flight, which is comprised of thrust, specific impulse, pressure recovery ratio, location of shock waves, and magnitude of drag, was predicted. The results show that compared to Rocket Assisted Projectile(RAP), the range was increased by 90 %. Furthermore, how variations in nozzle exit area ratio and the intake area cause variations in range was observed. This research on modeling and simulation methodology will provide useful data for future development of solid fuel ramjet projectiles.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.60-60
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• 2002

비행탄의 종말속도증대를 위하여 고체램제트를 이용하는 개념은 현재 세계적으로 여러나라에서 연구 중에 있다. Solid Fuel Ramjet Propulsion(고체연료 렘제트 추진)은 로켓추진에 비하여 월등히 높은 비추력을 가지며 구조적으로 매우 간단하여 탄의 사거리 및 평균속도를 증대시키는 좋은 수단으로 사용되고 있다. 그러나 간단한 구조에도 불구하고 고체렘제트의 작동은 매우 다양한 물리적 현상이 연관되므로 필요한 성능을 얻기 위해서는 이들의 상호 작용을 고려하여 설계의 최적화 및 성능 예측이 필요하다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.9 no.3
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• pp.261-268
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• 1985

본 연구의 목적은 외적요인으로서 바람과 내적요인들이 탄자에 영향을 미칠때 탄의 동적특성변화를 예측하는데 있다. 즉 탄의 X.Y.Z축 자취, .alpha.각(angle of atta- ck)의 변화, .PHI.와 .theta.의 관계 그리고 사각과 바람에 의한 탄의 동적특성변화등을 해석 하는데에 있다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.9
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• pp.62-68
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• 2018

This study was conducted to improve the shooting stability of self propelled artillery by improving the flick rammer system. The flick rammer system is designed to reduce crew fatigue and shorten the movement and loading time of the shell compared with the conventional manual loading system. Basically, in the flick rammer system of the shooting type, fall-back occurs intermittently, which causes problems in the rapid loading. To solve this problem, a detailed C.A.E. (Computer Aided Engineering) analysis of the internal structure of the existing rapid loading field was conducted. Through this, we sought a solution that can prevent fall-back by reducing the flying distance. We then optimized the loading station to reduce the flying distance and confirmed the possibility of suppressing the fall-back compared to the existing product through actual tests in the field.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.6
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• pp.502-511
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• 2016

Recently, many kind of smart projectiles are being developed. In case of smart projectile, studying in advance, it uses a navigation data acquired from the GNSS receiver to check its location on the geocentric(WGS84) coordinates and to estimate P.O.I(point of impact). However, because of various error inducing factors, the result of positioning involve some errors. We introduce the advanced algorithm for the reconstruction of a navigation trajectory using weighted PDOP, based on a simulated trajectory acquired from PRODAS. It is very fast and robust to noise and shows reliable output. It can be widely used to estimate an actual trajectory of a projectile.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.1
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• pp.98-103
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• 2017

In this paper, determination method for drag force and drag coefficient from results of firing test is described. The drag force and drag coefficient are determined through inverse operation of 2-dimensional projectile equation of motion. Determination method was verified by comparing analytical drag coefficient with data from flight test. Analysis of drag coefficient and drag reduction was performed with the data of flight test using artillery projectiles with base bleed unit.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.19-19
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• 1999

155mm 탄에 항력감소장치(Base Bleed Unit)를 부착하여 탄의 비행중에 형성되는 탄저부의 항력(Base Drag)을 감소시켜 사거리를 연장하는 무기체계가 미국을 비롯한 많은 국가에서 실용화되고 있다. 국내에서는 국과연 주관사업으로 이미 신형자주포에 적용되는 155mm 탄의 항력감소장치를 개발, 사거리 약 35%를 증가하여 실용화 단계에 있다. 또한 최근에는 미제 M864급인 155mm 성능개량 DPICM(Dual purpose Improved Conventional Munition)탄과 동등 성능을 갖는 탄의 개발이 요구되어, 이의 항력감소제인 저연소속도 추진제를 개발하여 155mm DPICM탄에 적용한 결과 약 20%의 사거리가 증가된 미제와 동등한 성능의 항력감소제를 개발하여, 이를 보고한바 있다.

• Journal of the Korea Society for Simulation
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• v.29 no.3
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• pp.49-55
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• 2020

A goal of improving projectile is to increasing achievable range. The shape of a projectile is generally selected on the basis of combined aerodynamics and structural considerations. The choice of body, nose and boattail shape has a large effect on aerodynamic design. One of the main design factors that affect projectile configuration is aerodynamic drag. The aerodynamic drag refers to the aerodynamic force that acts opposite to the relative motion of a projectile. An investigation was made to predict the effects of nose, boattail and body shapes on the aerodynamic characteristics of projectiles using a semi-empirical technique. A parametric study is conducted which includes different projectile geometry. Performance predictions of achievable range are conducted using a trajectory simulation model. The potential of extending the range of a projectile using optimization of projectile configuration is evaluated. The maximum range increase is achieved due to the combination of optimal body shapes.

• Defense and Technology
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• no.6 s.136
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• pp.28-35
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• 1990

재래식 총은 발사체의 속도가 너무 낮기 때문에 이동하는 목표물에 대한 명중률이 낮으므로, 현대전은 발사체 속도를 높이기를 요구한다. 이 문제는 대공화기에서 특히 절실하며, 그것은 공격하는 비행체의 속도와 고도 증가에 보조를 맞추지 못해 왔기 때문이다. 또한 실제적인 표적거동에 대하여 조준점과 탄착점과의 오차 거리는 비행시간의 제곱에 좌우되므로, 전자기 총은 사격제어 오차의 영향을 80-90%까지 감소시킬수 있다. 종말탄도 조건은 장갑두께가 변할 때 변하므로 대장갑 교전에서는 균일장갑에만 해당되나, 그럼에도 불구하고 대장갑 교전에서 장점이 기대된다

• Journal of the Korea Institute of Military Science and Technology
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• v.11 no.4
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• pp.5-12
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• 2008

There are some ways to improve precision of conventional munitions by low-cost method. 2D Course Correction Munition(CCM) is one of those ways, which is a 155mm projectile integrated with 2D Guidance Fuze(GF) instead of conventional fuze. 2D GF can correct the projectile trajectory and minimize range and deflection errors from its aimpoint using canard control. In this paper 2D CCM system concept is introduced and its course correction capability is analyzed using PRODAS.