• Journal of Astronomy and Space Sciences
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• 제15권2호
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• pp.509-523
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• 1998

군 통신위성 탑재 체의 개념모델(payload Concept Model; PCM) 연구는 실제 위성의 설계 및 제작 이전에 탑재 체를 지상에서 상용부품으로 구성하고 실제 위성과 가까운 통신전파 조건에서 시험하여 그 특성과 성능을 미리 파악하고자 하는 것이다. 본 논문에서는 이러한 통신 탑재 체 개념 모델을 구현하기 위한 기계구조물의 설계와 제작 과정을 기술하고 있다. 제작된 개념모델의 설계 조건의 만족여부를 검증하기 위하여 기본 RF 특성 시험을 실시하였으며 시스템이 양호한 통신품질을 제공함과 정상적으로 작동됨이 확인되었다.

• 시스템엔지니어링학술지
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• 제2권2호
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• pp.11-20
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• 2006

For systematic and effective achievement of Military R&D(Research and Development) processes and activities, information system which supports the concept of Systems Engineering is necessary. WISEMAN(Weapon System Information Integration for System Engineering and Management) is an information integration system, which can provide various kinds of interrelated application functions and assist the collaboration and concurrent engineering activities for weapon system R&D processes and activities. WISEMAN can manage the design information and configuration data of the target development products. It takes charge of the processes and histories about the product data, makes to share all the design information, and provides important application functions for R&D processes such as requirement management, product structure management, parts Management, documents and CAD drawing management, design change management, TDP(Technical Data Package) management etc., and in conjunction with these functions WISEMAN controls various effectivities of system configurations based on baselines and model information. WISEMAN has been used by ADD and Rotem Co. since developed.

• 한국군사과학기술학회지
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• 제13권6호
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• pp.1019-1025
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• 2010

This paper describes on methods in test and evaluation of the guided rocket munitions of the domestic new generation multiple launcher rocket system. We modified and refer to the present model of air-to-air missile(AAM) and surface-to-air missile(SAM). Also we suggested a method of surface-to-surface missile(SSM) based on the characteristics of the guided rocket in test and evaluation(T&E). According to this study, the suggested activity of T&E should be observed methods compatible with each item on the established model. Therefore, we expect that the proposed research material will be a good guide to the study of a surface-to-surface missile(SSM) installed GPS/INS integration navigation guidance & control systems in the future.

• 한국군사과학기술학회지
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• 제19권2호
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• pp.171-176
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• 2016

In this paper, the integration of the firing test stages at the acceptance test of the propelling charge has been studied using statistical analysis on the basis of the test data of K676 and K677 propelling charge for K9 self propelled howitzer. Acceptance test of K676 / K677 propelling charge consists of 3 stages and each stage is charge assessment test, charge uniformity test and charge proving ground test. Many of rounds are fired and much money is spent to prove the charge performance at each stage. The result of t-test shows that there is no difference between charge uniformity and charge proving ground test stage of K676 and K677 propelling charge.

• 한국군사과학기술학회지
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• 제17권2호
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• pp.189-196
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• 2014

Automated design program using commercial process integration and optimization program was developed for conceptual design of fighter-class aircraft. Wind tunnel test data and performance analysis results were compared for the verification of analysis tool of this program, and the usefulness of the tool was found. After integration with radar cross section analysis tool, the correlation with configuration design variables of wing, tail and performance parameters was identified by design of experiment, and the optimized configuration for weight and RCS was derived from optimization of empty weight and average frontal RCS value. After parameter definition of fuselage, the program can be implemented for full aircraft configuration.

• 한국군사과학기술학회지
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• 제27권3호
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• pp.387-394
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• 2024

This paper describes a progressive test and evaluation strategy for verification of Korean Fighter eXperimental (KF-X) AESA(Active Electronically Scanned Array) radar development. Three progressive stages of development test and evaluation were officially performed from simulated test conditions to actual operating conditions according to standards: radar function/performance and avionics integration. KF-X AESA radar development is repeatedly verified by progressive stages consisting of five tests: Roof-lab ground test, System Integration Laboratory(SIL) ground test, Flying Test Bed(FTB) test, KF-X ground test, and KF-X flight test. As a result, the risk factor decreases as stages and tests progress. Therefore, development test and evaluation of KF-X AESA radar are successfully performed at low development risk.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2008년도 추계학술대회논문집
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• pp.460-465
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• 2008

This paper proposes a new type of MR (magentorheological) fluid based suspension system and applies it to military vehicle for vibration control. The suspension system consists of gas spring and MR damper. The nonlinear behavior of spring characteristics is evaluated with respect to the wheel travel and damping force model due to viscosity and yield stress of MR fluid is derived. Subsequently, a military vehicle of 6WD is adopted for the integration of the MR suspension system and its nonlinear dynamic model is establishes by considering vertical, pitch and roll motion. Then, a sky-hook controller associated with semi-active actuating condition is designed to reduce the vibration. In order to demonstrate the effectiveness of the proposed MR suspension system, computer simulation is undertaken showing vibration control performance such as roll angle and pitch angle evaluated under bump and random road profiles.

• 한국소음진동공학회논문집
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• 제19권1호
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• pp.17-23
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• 2009

This paper proposes a new type of MR(magnetorheological) fluid based suspension system and applies it to military vehicle for vibration control. The suspension system consists of gas spring and MR damper. The nonlinear behavior of spring characteristics is evaluated with respect to the wheel travel and damping force model due to viscosity and yield stress of MR fluid is derived. Subsequently, a military vehicle of 6WD is adopted for the integration of the MR suspension system and its nonlinear dynamic model is established by considering vertical, pitch and roll motion. Then, a sky-hook controller associated with semi-active actuating condition is designed to reduce the imposed vibration. In order to demonstrate the effectiveness of the proposed MR suspension system, computer simulation is undertaken showing vibration control performance such as roll angle and pitch angle evaluated under bump and random road profiles.

• 한국컴퓨터정보학회논문지
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• 제24권6호
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• pp.99-107
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• 2019

With the development of various types of military Unmanned Aircraft(UA)s, the need for interworking and integration between different platforms gradually increased. In order to ensure interoperability at each military UA System(UAS) level, North Atlantic Treaty Organization(NATO) has established STANAG-4586 "Standard Interfaces of Unmanned Aircraft(UA) Control Systems(UCS) for NATO UA Interoperability-Interface Control Document". This paper looks at the basic design structure of STANAG-4586 and the changes on Edition 4 to enhance joint operational capability through reflecting and updating the interoperability design of the military UAS. In particular, we analyze the enhanced Datalink Transition/Handover Procedure and Autonomous functions, one of the biggest features added to the edition. Through this, we propose a modification of UA data link exclusive control using UA Bypass structure, which was impossible in the one-to-one communication structure between existing UA and Core UCS(CUCS). We also suggest ways to improve UA operational reliability by applying Autonomous Functions that directly decides how to deal with emergency situations, rather than by a remote operator over CUCS.

• 한국군사과학기술학회지
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• 제26권4호
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• pp.313-323
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• 2023

The wearable robot system is designed to assist human skeletal and muscular systems for enhancing user's abilities in various fields, including medical, industrial, and military. The military has an expanding need for wearable robots with the integration of surveillance/control systems and advanced equipment in unstructured battlefield environments. However, there is a lack of research on the design and mechanism of wearable robots, especially for power assist systems. This study proposes a lightweight wearable robot system that provides comfortable wear and muscle support effects in various movements for soldiers performing high-strength and endurance missions. The Power assist mechanism is described and verified, and the tasks that require power assist are analyzed. This study explain the system including its driving mechanism, control system, and mechanical design. Finally, the performance of the robot is verified through experiments and evaluations, demonstrating its effectiveness in muscle support.