• 대한산업공학회지
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• 제3권2호
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• pp.73-81
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• 1977

Mission effectiveness, which is the probability of successfully completing the assigned mission, is introduced as an appropriate measure of effectiveness for a military system. The model of mission effectiveness is developed for a system which is required to carry out various types of a mission. Each mission type is characterized by the maximum allowable time that determines the success of a given mission type. A given type of a mission is successful if and only if (i) the system is available at the start of a mission and (ii) the system completes its mission within the maximum allowable duration of time that this given mission type specifies without any failure during this period. Both analytic and simulation approaches are employed. Difficulties involved in the anayticl approach are discussed. The model is proposed as a useful tool for consistent system evaluation and optimum test design.

• Journal of electromagnetic engineering and science
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• 제3권1호
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• pp.12-16
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• 2003

In this paper, low noise amplifiers with coplanar waveguide structure are presented for Wireless LAN data communication application. For comparison of microwave performance, LNAs of cascode type and balanced type using cascode cell with the same substrate and same bias conditions are designed and implemented. A cascode type of LNA shows the gain of 12.45 ㏈, input return loss of 11.63 ㏈, and noise figure of 1.52㏈. A balanced type of LNA using cascode cell shows the gain of 6.58 ㏈, input return loss of 16.6 ㏈, and noise figure of 1.18 ㏈.

• 한국군사과학기술학회지
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• 제13권2호
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• pp.180-187
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• 2010

In this paper, a global path generation method is suggested using multiple grid maps connected with the mission type of unmanned combat vehicle(UCV). In order to carry out a mission for UCV, it is essential to find a global path which is coincident with the characteristics of the mission. This can be done by considering various combat circumstances represented as grid maps such as velocity map, threat map and communication map. Cost functions of multiple grid maps are linearly combined and normalized to them simultaneously for the path generation. The proposed method is realized using $A^*$, a well known search algorithm, and cost functions are normalized in the ratio of the traverse time which is one of critical information should be provided with the operators using the velocity map. By the experiments, it is checked found global paths match with the mission type by reflecting input data of grid maps properly and the computation time is short enough to regenerate paths in real time as combat circumstances change.

• 한국국방경영분석학회지
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• 제15권1호
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• pp.14-27
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• 1989

This paper deals with the mission effectiveness of an airfleet, Airfleet operating system consists of a finite number of units performing the several mission types. Earlier works for the mission effectiveness of a fleet is limited to only one mission type and computer simulation approaches. The mission effectiveness. model of a fleet is constructed by three attributes - the mission readiness of the units, the mission reliability and capability of units. The environmental conditions and human factors affecting the mission success are considered together. The solution of the model is obtained by analytical technique. Especially, AOS is considered a closed queueing network with a finite number of units and a single job class. And then, the mission readiness of the units is found by the mean value analysis. The model would be a useful tool to readily evaluate mission effectiveness of a airfleet as it is and provide a criterion for determining the optimal operating policy.

• International Journal of Aeronautical and Space Sciences
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• 제14권2호
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• pp.162-171
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• 2013

A general purpose aircraft mission performance analysis program has been developed. The program can be used in design mode or in analysis mode. Fuel weight for a given mission profile can be estimated when the design mode is chosen, while mission time or mission range for a given fuel can be estimated when the analysis mode is chosen. The mission analysis program is written with JAVA and includes GUI(Graphic User Interface) for users' conveniences. With a proper combination of databases for propulsion, aerodynamics and weight, the program can be configured to compute the performance of any type of aircraft. The program is validated by comparing its results with the results of a well known performance analysis program by ADD(Agency for Defense Development).

• 천문학회보
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• 제32권2호
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• pp.41.2-41.2
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• 2007

• Strategy21
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• 통권46호
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• pp.205-238
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• 2020

The origin of mission command can be traced to the era of the Prussian military reforms led by General Gerhard von Scharnhorst after defeats in battle of Jena and Auerstadt in 1806 against Napoleon I. Mission Command is the conduct of military operations through decentralized execution based upon mission-type orders. Commanders issue mission-type orders focused on the purpose of the operation rather than details of how to perform assigned tasks. The mission command has become the command philosophy of the German military and recently many countries in the west accept it as a command philosophy. This study compare and analyze the Battle of St. Vincent and the Battle of Jutland to make sure if the army-initiated mission commands were also useful for the navy. From the late 18th century, represented by the era of Nelson, Royal navy changed from the inherited rigid command culture to guaranteeing the disciplined initiative of its subordinate commanders. In the Battle of St. Vincent in 1797, Nelson acted contrary to the commander's orders at the crucial moment, which gave Britain a decisive victory. On the contrary more than 100 years later, the command culture of the Royal navy changed into a centralized command culture. In the Battle of Jutland in 1916, Royal Navy couldn't win because the rigid command culture did not guarantee initiative of subordinate commanders and subordinate commander's passive attitude of waiting for the commander's instructions even at critical moments. Therefore, a mission command that guarantees the initiative of subordinate commanders is a useful concept even in the navy because it makes subordinate commanders to take full advantage of a sudden change in battle. Today's advanced information and communication technologies have raised questions about mission command. But even advanced technology can't completely eliminate the fundamental nature of the war-the fog of war. War is chaotic and unpredictable. In the flood of lots of informations, senior commander's judgement is not always right because he(she) is also human, he(she) can make mistakes. In the age of informatization, mission command is still effective because it involves increasing interaction and synergy between senior and subordinate commanders by ensuring their independence. Therefore ROK navy also needs to activate mission command. ROK navy must dismantle the zero-defect mentality and apply from educations as Prussian did to establish a mission command culture.

• 항공우주기술
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• 제2권2호
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• pp.96-104
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• 2003

정지궤도 인공위성의 추진시스템은 위성발사에서부터 모든 임무궤도의 자세제어와 마지막 임무단계인 폐기궤도 기동을 위한 다양한 속도증분을 제공한다. 이러한 추진시스템은 위성제작사에 따라 매우 다양하게 구성되고 있으며 버스체마다 사용되는 추력기 또한 매우 다양하다. 따라서 각 정지궤도위성 제작사에서는 각각의 추진시스템에 맞는 모든 궤도 관련 임무를 계획하고 검증하는 임무해석소프트웨어를 개발하고 있다. 이러한 범용화된 임무해석소프트웨어를 개발하기 위하여 다양한 추력기 데이터를 검토하였고 이를 토대로 일반화된 추력기 모델링식을 구축하였다.

• International Journal of Aeronautical and Space Sciences
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• 제5권2호
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• pp.54-61
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• 2004

In this paper we carried out a design study for an unmanned Mars missionsuitable for Republic of Korea. The mission will use a KSLV series launch system,which is to place a one tonne payload into the LEO. We calculated the velocityincrements(AV) required for departure from Earth and insertion into the orbitaround Mars based on the mission opportunity data provided by NASA. Two typesof Mars modules - entry type and orbiter type - were considered in this studyWe calculated the mass of TPS(therma1 protection system) for the entry tvpe Marsmodule based on the heat transfer rate and heat load from the Mars atmosphere tothe surface of the TPS. The heat transfer rate and heat load were obtained throughan entry trajectory calculation. For the orbiter type Mars module, we calcuIated themass breakdown of the additional spacecraft which is to insert the Mars moduleinto the orbit around Mars. Other mass items were determined by proportioningfrom the existing Mars modules. This paper finally proposes the payload capacitiesfor each types of Mars modules.

• 한국산학기술학회논문지
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• 제21권7호
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• pp.156-161
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• 2020

복수 무인기를 운영하는 환경에서 분산 임무 할당 알고리즘의 사용은 임무를 지휘 통제하는 중앙 관제 시스템이 없기 때문에 중앙 집중식 임무 할당 방식에 비해 무인기의 임무 중 탈락 이벤트로부터 보다 큰 강건성을 가지게 된다. 또한 무인기 스스로 상황을 인지하고 통신을 통해 임무를 재할당 하는 방식이기 때문에 임무 반경 또한 더욱 넓힐 수 있는 장점을 가지고 있다. 하드웨어 성능이 향상되고 비용이 감소함에 따라 임무 환경에서의 복수 무인기 운용에 대한 필요성이 증대되고 있으며, 작전 반경이 넓고 단일 고장에 강건한 분산 임무 할당 알고리즘에 대한 연구 필요성이 대두되고 있다. 본 논문은 대표적인 분산 임무할당 알고리즘인 CBBA를 기반으로 하여, 기존에 점 좌표로 단순화 되어 설정된 임무 종류를 점 좌표에 대한 감시 업무와 선형 경로의 정찰 임무로 구분하여 보다 현실에서의 임무 상황을 반영할 수 있도록 발전시켰다. 본 연구의 결과로서 복수무인기가 과다 임무가 부여된 상황에서 동일한 임무위치 및 보상을 갖는 상황을 몬테 카를로 시뮬레이션을 통해 최종 보상합(global reward)을 비교한다.