• 시스템엔지니어링학술지
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• 제10권2호
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• pp.89-95
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• 2014

In recent years, the United States have been several major failures of launch. As a result of these failures, activity of mission assurance valued. Mission assurance is defined as the application of systems engineering process towards the goal of achieving mission success. Therefore, mission assurance perform independent technical assessments throughout the concept and requirements definition, design, development, production, test, deployment, and operations phases. Space system program was emphasized the importance of the system engineering for that required huge cost and long term development. For this reason, independent review and verification of mission assurance is essential. Mission assurance gives us confidence to proceed with launch and best opportunity for mission success. In this study, framework of mission assurance is proposed by foreign case analysis.

• 산업진흥연구
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• 제9권1호
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• pp.249-257
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• 2024

본 연구는 중국 청년 교사를 대상으로 진로지속학습이 직업적 사명감을 경유하여 진로성공에 미치는 영향에서 진로개발압력의 조건부 직접효과를 확인하는데 연구의 목적이 있다. 자료는 중국 광동지역의 한 대학교에서 유의표집한 청년 교사 354명을 대상으로 설문조사를 통하여 수집하였다. 수집한 자료는 SPSS PC+ Win ver. 25.0과 SPSS PROCESS macro ver. 4.2를 활용하여 분석하였다. 적용된 통계방법은 빈도분석, 신뢰도 분석, 상관분석 및 조건부직접효과 분석이었다. 연구의 결론은 다음과 같다. 첫째, 진로지속학습 및 직업적 사명감은 진로성공과 유의한 양의 상관관계가 있었으나, 진로개발압력과는 유의미한 상관관계가 없는 것으로 나타났다. 진로개발압력은 진로성공과 유의한 음의 상관관계를 보였다. 둘째, 진로지속학습이 직업적 사명감을 경유하여 진로성공에 미치는 영향에서 진로개발압력의 조건부 직접효과가 확인되었다. 이러한 결과를 토대로 본 연구는 대학생들의 진로지속학습 뿐만 아니라 직업적 사명감과 진로개발압력을 동시에 활용하여 진로성공을 증진할 수 있는 방안을 제시하였다.

• 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.

• 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.

• 항공우주시스템공학회지
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• 제9권2호
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• pp.41-46
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• 2015

The various risk factors that affected schedule, costs and mission success, etc. in development of the satellite. This paper derives the considerable "Cost of Quality" factors in the satellite development phase through the survey of practical techniques in respect of measurement of quality cost in the commercial products manufacturing, and proposes mitigation strategy of quality cost using the approach that can be minimized it.

• 한국해양공학회지
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• 제36권3호
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• pp.181-193
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• 2022

This study presents a mission management technique that is a key component of underwater docking system used to expand the operating range of autonomous underwater vehicle (AUV). We analyzed the docking scenario and AUV operating environment, defining the feasible initial area (FIA) level, event level, and global path (GP) command to improve the rate of docking success and AUV safety. Non-holonomic constraints, mounted sensor characteristic, AUV and mission state, and AUV behavior were considered. Using AUV and docking station, we conducted experiments on land and at sea. The first test was conducted on land to prevent loss and damage of the AUV and verify stability and interconnection with other algorithms; it performed well in normal and abnormal situations. Subsequently, we attempted to dock under the sea and verified its performance; it also worked well in a sea environment. In this study, we presented the mission management technique and showed its performance. We demonstrated AUV docking with this algorithm and verified that the rate of docking success was higher compared to those obtained in other studies.

• 융복합기술연구소 논문집
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• 제5권1호
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• pp.19-22
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• 2015

Human powered aircraft (HPA) is an airplane that uses only human power for its propulsion. The human power as a power resource and an engine produce the available power that is very crucial to the success of the HPA. In the present paper, the human power characteristics for completing the mission profile are discussed focusing on the take-off and climbing performance. The mission profile is designed by using an athlete's power generation. It is believed that present analysis can be helpful for the mission profile design and athletes exercise program development for the HPA competitions.

• International Journal of Human Ecology
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• 제11권2호
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• pp.77-91
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• 2010

This study examined the Family and Consumer Sciences (FCS) National Standards with some examples at the state level, analyzed the previous studies relevant to curriculum implementation in the USA, and explored critical success factors in moving toward the new perspective curriculum in exemplary states. The process, in which the FCS discipline struggled to clarify the identity and image as well as to find the mission and vision, produced the FCS National Standards in 1998 and 2008 in the USA. The FCS National Standards were established to fulfill the mission of the FCS based on a critical science perspective. The previous research on a state level implementation indicated that the majority of FCS state administrators agreed that the National Standards positively influenced curriculum development. The critical success factors in integrating National Standards into local programs included the dissemination of thephilosophical works of Marjorie Brown, the foundation of the FCS curriculum with a critical science perspective, the establishment of National Standards corresponding to the philosophical works and a critical science perspective, the openness of state FCS administrators to educational reform, the construction of an infrastructure to support reform, and the commitment by university professors to develop a teacher training program. The critical success factors identified can be employed as an informative guide for the future development and implementation of the Family and Consumer Sciences curriculum in Korea.

• Journal of Astronomy and Space Sciences
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• 제32권3호
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• pp.257-268
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• 2015

Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements. Results provided through this work will be helpful in further detailed system definition and design activities for future lunar missions with a CubeSat-based payload.

• 천문학논총
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• 제30권2호
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• pp.621-624
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• 2015

We present the current status (as of August 2014) of SPICA (Space Infrared Telescope for Cosmology and Astrophysics), which is a mission optimized for mid- and far-infrared astronomy with a cryogenically cooled 3m-class telescope. SPICA is expected to achieve high spatial resolution and unprecedented sensitivity in the mid- and far-infrared, which will enable us to address a number of key problems in present-day astronomy, ranging from the star-formation history of the universe to the formation of planets. We have carried out the "Risk Mitigation Phase" activity, in which key technologies essential to the realization of the mission have been extensively developed. Consequently, technical risks for the success of the mission have been significantly mitigated. Along with these technical activities, the international collaboration framework of SPICA has been revisited, which resulted in la arger contribution from ESA than that in the original plan. To enable the ESA participation under the new framework, a SPICA proposal to ESA is under consideration as a medium-class mission under the framework of the ESA Cosmic Vision. The target launch year of SPICA under the new framework is the mid-2020s.