• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.11
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• pp.755-762
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• 2022

The wind tunnel test data for the missile configuration were compared with analysis results using various semi-empirical code and CFD analysis code. The three types of configurations were used for comparison including 2 types of main wing, inline and interdigitate configuration that the main wing and tail intersect. Additionally, it was confirmed that the vortex flow was accurately predicted by comparing the CFD analysis result with the flow visualization test result.

• Journal of the Korea Society for Simulation
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• v.29 no.1
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• pp.1-9
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• 2020

The ballistic missile threat continues to increase with the proliferation of missile technology. In response to this threat, many kinds of interceptors have been emphasized over the years. For development of interceptor, systematic flight tests are essential. Flight tests provide valuable data that can be used to verify performance and confirm the technological progress of ballistic missile defense system including interceptor. However, during flight tests, civilians near the test region could be risk due to a lot of intercept debris. For this reason, reliable estimate of safety area for the flight tests should be preceded. In this study, prediction of safety area is performed through modeling and simulation. Firstly, behaviors of ballistic missile and interceptor are simulated for those entire phase including interception to obtain the relative intercept velocity and the relative impact angle. By using obtained data of kinetic energy, the fragment ejection velocity is calculated and fragment trajectories are simulated by considering drag, gravity and wind effects. Based on the debris field formation and hazard evaluation of debris, final safety area is calculated.

• The Korean Journal of Air & Space Law and Policy
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• v.24 no.2
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• pp.211-234
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• 2009

North Korea conducted the launcher test, which, as North Korea claimed, belonged to the sovereign rights for the purpose of peaceful utilization and exploration of the outer space. The launching was allegedly done for the sole purpose of putting the satellite into earth orbit, while international community stressed the fact that the orbiting of satellite was not confirmed and that the technology used was not distinct from the purpose of building intercontinental ballistic missile. UN Security Council adopted the resolutions which took the effect that the launching was deemed as the missile launching, not the mere launcher test. North Korea declared the moratorium of suspending its test activity. Controversial issues have been raised regarding whether the launcher itself has the legal status of enjoying the freedom of space flight based upon the 1967 Outer Space Treaty. The resolutions, however, has put forward a binding instrument forbidding the launching. UN Security Council resolutions, however, should be read not as defining the missile test illegal, in that the language of resolutions, such as 'demand', should be considered as not formulating a sort of obligatory act or inact. On the other hand, the resolutions should be read as having binding force with respect to any activity relating to the weapons of mass destruction. The resolution 1718 is written in more specific language such as 'decides that the DPRK shall suspend all activities related to its ballistic missile programme and in this context re-establish its pre-existing commitments to a moratorium on missile launching'. Therefore, the lauching activity of the North Korea is banned by the UN Security Council resolution. It should be noted that the resolution does not include any specific provisions defining the space of activity of the North Korea as illegal. But, the legal effect of the moratorium is not denied as to its launching itself, which is corresponding to the missile test clearisibanned in accordance with the resolutions.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.3
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• pp.360-368
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• 2019

A study on aerodynamic modeling was performed to predict the hinge moments required for initial design of missile. Fin aerodynamic coefficients were modeled using the equivalent angle of attack method based on the wind tunnel test. In addition, CFD analysis was performed to calculate the dynamic pressure around the body and improve the accuracy of aerodynamic coefficients. The aerodynamic coefficient accuracy was verified by comparisons of the coefficient acquired from wind tunnel test and prediction of flow conditions, not involved in the model built-up. It was confirmed that fin aerodynamic coefficients can be predicted effectively by using the proposed method.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.1
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• pp.268-277
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• 2019

Flight test systems should monitor various conditions in real time during flight tests and take safety measures in an emergency. The importance of ensuring test safety increases in more complicated and wider test environments. Also, due to the transition of wartime operational authority, many guided missile systems must be developed simultaneously. Early deployment and budget reduction by shortening the development and T&E periods are also necessary. Consequently, the risk of flight tests under the circumstance of inefficient test resources is increasing. To address this deficiency, a flight test system model using SysML was proposed in this study. The method of designing and verifying the test system is based on the agile shift left testing methodology of advanced T&E labs and utilizing a system reference model in the aerospace field. Through modeling and simulation analysis, early identification and correction of faults resulting from inconsistent test requirements can mitigate the risk of delays during the T&E phase of flight tests. Also, because the flight test system model was constructed using SysML, it can be applied to test various guided missile systems.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.19 no.8
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• pp.1965-1972
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• 2015

The Missile Flight Test Launch Control System is to operate in conjunction with the Fire Control System during flight test to guided weapons. Also, this is a system for the test control and situation monitoring depending on the type of guided weapons and testing purposes. Message structure, communication protocols, such as data types for interworking with the fire control system and the Missile Flight Test Launch Control System are defined in the Launch Control ICD(Interface Control Document). ICD are composed differently of each guided weapons system and each test object. Previously, in order to interwork with the Fire Control System, the interlocking software was developed, which had a variety of problems. Therefore, we developed a new parsing algorithm in order to recognize the variety of Launch Control ICD and verified that the algorithm operates normally by checking transmitting and receiving various message in conjunction with the fire control system.

• Journal of the Korea Society for Simulation
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• v.27 no.1
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• pp.111-117
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• 2018

It is indispensable for a missile to track a target under the flight condition since the tracking capability affects the system performance considerably. The best way to verify the tracker's performance is flight test while it costs too much. Consequently, captive flight test or CFT has an important role in the development of a missile system. CFT, however, cannot simulate missile dynamics and is an offline and open-loop test. In this paper, we propose a new integrated-flight simulation(IFS) method using CFT imagery to overcome the limitation of synthetic image-based IFS method. This method increases the utilization of CFT's outputs and compensates the reality of imagery which lacks in the synthetic image-based IFS. Using this method make it possible to verify the system capability in various simulation modes.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.45-48
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• 2003

The plume interference is a complex phenomenon, consisting of plume-induced boundary layer separation, separated shear layer, multiple shock waves, and their interactions. The base knowledge of plume interference effect on powered missiles and flight vehicles is not yet adequate to get an overall insight of the flow physics in plume-freestream flow field. Computational studies are performed to better understand the flow physics of the plume-induced shock and separation for Simple, Rounded, Porous-extension test model configurations. The present study simulates highly underexpanded exhaust plume effect on missile body at the transoni $c^ersonic speeds. In order to investigate the plume-induced separation phenomenon, Simple, Rounded and Porous-extension plate are attacked to the missile afterbody. The computational result shows that the rounded afterbody and the porous-extension wall attached at the missile base can alleviate the plume-induced shock wave and separation phenomenon and improve the control of the missile body.dy.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2659-2661
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• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.4
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• pp.536-542
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• 2017

In this paper, authors described on localization development's results about an electric igniter in thermal battery with a pyrotechnic heat sources. Especially, the development test and evaluation(DT&E) process and the methods in the developments of the electric igniter which is parts of a domestic thermal battery on K-PSAM was in charge of government and developed for defense of a local areas in Korea. We have proposed a process of design and manufacture on the electric igniter. Finally, we verified a quality and a reliability of the electric igniter from test results by Fisher-Snedecor's law and over 99.5 %(C.L. 95 %) for K-PSAM.