• Journal of the military operations research society of Korea
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• v.33 no.1
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• pp.117-133
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• 2007

The weapon accuracy is a basic measure of performance in the area of weapon system acquisition. It requires the establishment of correct concept and the T&E methods. Existing T&E method for aircraft weapon systems have not considered types of exact hitting area for various weapons. This study intends to suggest an optimal T&E methods in Korean T&E environment. In order to sampling and to test aircraft weapon accuracy, we need probability and statistic theories. There are many types of CEP(Circular Error Probable) methods. We recommend 2 types of CEP methods which are Lockheed Martin CEP method and Johnson CEP method. Also, suggest some other T&E methods. These methods can be used to accuracy test in the area of weapon system acquisition in the future.

• Journal of Advanced Navigation Technology
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• v.25 no.5
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• pp.377-383
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• 2021

In this paper, we describe the case of automatic test equipment development for hardware verification of stores management computer mounted on aircraft. Recently, the required functions of aircraft have been diversified and the related technologies of avionics equipment have developed, and the types and quantity of interfaces required for avionics equipment have increased. In addition to the existing old stores, the stores management computer also needs to control the interface in large quantities as the requirements for the new stores are added. For this reason, the time and manpower required for the inspection of avionic equipment are also increasing, and if the test process of avionic equipment can be automated and unmanned, more efficient inspection system operation will be possible. Therefore, this paper introduces the case of designing test software and test scenario to automate the structural design contents and verification process of test equipment required for the verification of hardware function of stores management computer.

• Proceedings of the Korean Society of Computer Information Conference
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• 2020.01a
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• pp.35-36
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• 2020

본 연구는 TA-50 항공기 임무컴퓨터에서 JDAM을 가상으로 운용하는데 필요한 소프트웨어 개선 내용 중 가상 JDAM 무장 투하 구역 계산 방법을 제안한다. 이 연구에서 제안한 무장투하구역 알고리즘은 FA-50 JDAM DLZ에서 추출한 무장투하구역 입/출력값을 tensorflow를 사용하여 학습한 알고리즘이다. 이 연구를 통해 제안한 가상 JDAM DLZ 알고리즘을 사용할 경우 실제 무장을 장착하지 않은 항공기에서 가상으로 JDAM 무장 투하 구역 표시가 가능하고, 조종사는 가상의 JDAM DLZ를 참고하여 무장 투하 훈련을 수행할 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.8
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• pp.741-746
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• 2007

In this paper, we propose an accuracy analysis method for air-to-ground weapon delivery. The lethality, which is one of the most important factor to evaluate combat effectiveness of a fighter, depends on the capability to improve the accuracy of the conventional weapon delivery. We present error elements which affect the error analysis for air-to-ground weapon delivery from the initial design phase to the final validation phase. And we introduce an accuracy analysis method to reflect the error elements and to evaluate them quantitatively. We assume zero bias-error and consider random error for the weapon delivery accuracy analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.12
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• pp.856-864
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• 2019

The weapon-target assignment (WTA) problem is a matter of effectively allocating weapons to a number of threats. The WTA in a rapidly changing dynamic environment of engagement must take into account both of properties of the threat and the weapon and the effect of the previous decision. We propose a method of applying the Greedy Randomized Adaptive Search Procedure (GRASP) algorithm, a kind of meta-heuristic method, to derive optimal solution for a dynamic WTA problem. Firstly, we define a dynamic WTA problem and formulate a mathematical model for applying the algorithm. For the purpose of the assignment strategy, the objective function is defined and time-varying constraints are considered. The dynamic WTA problem is then solved by applying the GRASP algorithm. The optimal solution characteristics of the formalized dynamic WTA problem are analyzed through the simulation, and the algorithm performance is verified via the Monte-Carlo simulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.5
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• pp.381-389
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• 2007

6-DOF simulation program is developed in order to increase the efficiency of the store separation analysis. This S/W is much faster than a method based on CFD(Computational Fluid Dynamics) technology, and allows the simulation of stores with fixed shape as well as with extensible wings, because it uses aerodynamic databases which are prepared beforehand. In this paper, aerodynamic databases of stores are obtained with MSAP(Multi-body Separation Analysis Program), and unsteady damping coefficients are modeled with Missile Datcom. These databases and the 6-DOF simulation program are used to predict the trajectory of an external store, while its wings are being deployed. The analysis results indicate that the safe separations of the store can be achieved not only with the wing fixed but with the wings being deployed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.124-133
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• 2003

We propose an application of the Object-Oriented design methodology to develop operational flight program(OFP) for stores management computer(SMC) which manages and controls stores inventory, stores activation, launch for missiles, and release of the conventional weapons. For the development of SMC, a military version of PowerPC 603e is used as a central processing unit board and VxWorks real-time operating system is used. The Tornado software development environment(SDE) and the programming language Ada95 are used for OFP development. We design three layerd in the OFP for the independency of the software modules. An avionics system computer(ASC) simulator and a test bench are developed for the SMC integration test and verification test. And the tests are rigorously and successfully conducted.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.4
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• pp.233-240
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• 2022

The smart weapon system is a new weapon system of the future battlefield environment as a miniature guided weapon that performs precision strike missions through terminal phase guidance. However, it has small coverage to guide due to its low maneuverability because the smart weapon is controlled by using actuator of piezoelectric drive type due to the structural limitations. In this paper, we propose a firing data calculation algorithm under non-standard conditions to increase the effectiveness of the smart weapon. The proposed algorithm calculates firing data under non-standard conditions by calibrating firing data under standard conditions using information acquired in battlefield environments. The performance of the proposed algorithm is verified by numerical simulations under various conditions.

• Defense and Technology
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• no.8 s.150
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• pp.76-79
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• 1991

오늘날 지상군을 지원하기 위한 근접 항공지원(CAS)은 무장투하의 정확성과 타이밍에서 괄목할만한 발전을 하였다. 특히 미국은 서방세계 국가들에 널리 통용되는 근접 항공지원의 유형을 창출하는데 큰 기여를 하였다. 그러나 미국 공군이 앞으로 지향하려는 방향에 대해서는 그 적용기술의 타당성 여부가 증명되지 않아 많은 비판에 직면해 있다. 이 시점에서 우리가 어디에 와 있고, 앞으로 어디로 갈 것인가를 점검해 보는 것은 아시아 국가들의 공군으로서는 의미있는 일이라고 사료된다

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.2
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• pp.106-112
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• 2005

Modern versions of supersonic jet fighter aircraft have several different weapon loading configuration to support air-to-air combat and air-to-ground delivery of weapon modes. These various aircraft loading conditions could result in asymmetric configurations to the aircraft once delivered. These asymmetric configurations could result in decreased handling qualities for the pilot maneuvering, stability, control issues and aerodynamic performance of the aircraft. In order to eliminate or decrease these adverse impacts on the pilot's ability, development of T-50 flight control law attempts to control the aircraft in both longitudinal and lateral-directional axes. Especially, the design of the lateral-directional roll axis control laws, utilizing a simple roll rate feedback structure and gains such as F-16, is developed for the T-50 aircraft to meet the aircraft's design requirements. Consequently, it is found that the improved control law decreases the roll-off phenomenon in lateral axes during pitch maneuver.