• Journal of Korean Society for Quality Management
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• v.44 no.3
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• pp.553-564
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• 2016

Purpose: The purpose of this study was to propose useful suggestions by analyzing reliability of guided missile using field data in Military industry. Methods: The collected data from Defense industry company and the military were analyzed using probit analysis which is non-linear model because field data contain binary variable. Results: The results of this study are as follows; It was found that the effect of time was significant. It takes about 12.4 years when 10st percentile of guided missiles are not working and it takes about 18.6 years when 50st percentile of guided missiles are not working. It was found that period between 10years to 15years comes less than reliability 0.0. Conclusion: Periodical check needs to extend from 4 year to 10 year partially. Early LOT need to check per 4 year and follow-up LOT extend the period of check to 10 year by reflecting the result of reliability.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.40 no.1
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• pp.209-216
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• 2015

It is difficult to detect, track and intercept ballistic missile because of its high speed and short flight time from launching to target area. In order to increase the success rate of a ballistic missile interceptor, it is important to track the flight trajectory for a long time after the detection in the early launch. Radar Cross Section(RCS) of the target is important when the target to be detected by the radar, and the difference between the RCS value greatly changes depending on the viewing direction during the flight missile trajectory. In this paper, it is assumed that a ballistic missile is launched at east coast of North Korea, observe that missile by a land based radar and sea deployed radar. And it is analyzed and compared that RCS difference of ballistic missile.

• Journal of the Korean Society for Precision Engineering
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• v.33 no.10
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• pp.781-787
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• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• International Journal of Aeronautical and Space Sciences
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• v.16 no.2
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• pp.148-156
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• 2015

A continuous type side jet controller which has four nozzles with thrust control devices was considered. It is deployed to a missile for high maneuverability and fast controllability in the terminal guidance phase. However, it causes more complex aerodynamic jet interactions between the side jet and the supersonic free stream than does the conventional impulse type side jet with a small single thruster. In this paper, a numerical investigation of the jet interference effects for the missile equipped with a continuous type side jet thruster is presented. A three-dimensional flow field was simulated by using a commercial unstructured-based CFD solver. The numerical simulation method was validated through comparison with wind tunnel test results for the single jet. The method of defining jet direction for this type of side jet control to minimize simulation cases was also introduced. Flow fields investigation and jet interaction effects for various flow conditions, jet pressure ratios and defined jet direction conditions were performed. From the numerical simulation for the continuous type side jet, extensive aerodynamic interference data were obtained to construct an aerodynamic coefficients database for precise missile control.

• Journal of Advanced Navigation Technology
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• v.24 no.5
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• pp.423-429
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• 2020

In this paper, the electromagnetic compatibility (EMC) test standard is described, and the purpose and test configuration for the electromagnetic susceptibility (EMS) test of the missile component and the missile system are confirmed. The test configuration and specifications are suggested by the configuration of the missile component and the missile system based on the US military standards MIL-STD-461F and MIL-STD-464C, and explained that the ungrounded state, the final operating state of the missile component and the missile system, was constructed. In addition, the methods for checking the steady state and the points to be considered during the immunity test were introduced.

• Journal of Advanced Navigation Technology
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• v.22 no.6
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• pp.500-506
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• 2018

In this paper, we considered the one-shot alignment using master inertial navigation system (MINS) and slave inertial navigation system (SINS) in the missile to find the exact posture of a missile. In order to perform one-shot alignment, the tilt angle between MINS and SINS must be obtained, which can be compensated by obtaining the tilt angle between missile round and SINS. The tilt angle was calculated by using the roll rotation of missile round, jig for rotating the missile round and interface structure to measure the horizontal state by using a horizontal angle meter were constructed. As a result of the tilt angle save (TAS) inspection, the tilt angle ${\alpha}$, ${\beta}$, ${\gamma}$ is normal range and it is possible to perform one-shot alignment by compensating this value.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.4
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• pp.349-357
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• 2017

If an actuation system of the tactical missile is required very fast response time on conditions of short operating time and big loads on the actuator, we would prefer to adopt a small hydraulic system. In this paper, a mathematical model is proposed to analyze and simulate the small hydraulic actuation system. The mathematical model consists of a high pressure vessel model, a pressure regulator model, a hydraulic reservoir model and a actuator model. The suggested model is validated by comparison of simulation results with experimental data. The simulation results show that the mathematical model could be useful for designing a hydraulic actuation system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.359-365
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• 2022

Air-to-ground missile(AGM), which can be operated by being mounted on the outside of the aircraft, is capable of precision strikes, ensuring high survivability. Helicopter, which is one of the AGM operating platforms, is reported to experience a lightning strike once between 1000 and 20000 flight hours in average. When the lightning strikes the helicopter fuselage, lightning transient signal can be induced to internal and external electronic equipment cables through the skin of the helicopter. If the transient signal exceeding the criteria to electrically initiated device(EID) related to the explosive in the AGM can affect the safety of the helicopter by a warhead explosion, etc. In this paper, we suggest an indirect lightning test method to prove the safety of AGM on helicopter, and present the indirect lightning test results.

• Journal of the Korea Institute of Military Science and Technology
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• v.23 no.2
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• pp.176-184
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• 2020

In this paper, we have proposed hardware and software architecture of a launch control unit for the compatibility between air defense weapon systems loaded on shipboard. Until now, there is no compatibility between weapon systems loaded in battleships of korean navy. In the case of HaeGung system recently completed the test and evaluations, although it will be deployed on several kinds of shipboards, it has no compatibility and flexibility with other air defense weapon systems. Recently it reports that a long range air defense weapon system will be carried on future korean destroyer KDDX. Because the HaeGung and a long range air defense system will be operated together in KDDX, it is necessary to provide the compatibility between two weapon systems. So we have proposed architecture to provide the compatibility of the launch control unit that controls the launching system and the missile interface unit, and the missile in each weapon systems.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.23 no.2
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• pp.266-269
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• 2012

This paper introduces a signal processing technique for discrimination of ballistic missile's warhead. An interceptor missile to destroy the enemy's ballistic missile requires an information on the location of missile's warhead. In order to detect and locate the missile's warhead, a seeker radar in the interceptor missile makes use of chirp waveform to generate high resolution range profiles(HRRPs). We applied one of the well known spectral estimation technique called ESPRIT (Estimation of Signal Parameters by Rotational Invariance Technique) to these HRRPs to estimate scattering centers on the target. Using the information on the one-dimensional(1-D) scattering centers, we can find the location of the warhead by estimating the length of the missile, Simulation results show that the proposed signal processing technique is efficient in discriminating the warhead of an ballistic missile.