분리막 공정은 압력장치에 사용되는 전기 사용량이 많아 이를 줄이기 위한 다양한 공정 옵션이 연구되고 있다. 본 연구에서는 분리막 공정에서 막 모듈에 sweeping 기체를 permeate에 불어넣어 모듈의 구동력을 증가시키는 방법으로, 특별한 공정 장치 추가 없이도, 효율적인 CO2 분리가 되는 공정을 연구하였다. 분리막 공정은 주요 장치비용(분리막, 압축기 등)과 운영비용(전기, 스팀)을 평가 하였다. MATLABⓇ에서 분리막 모델을 개발하었으며, 분리막 공정에 가능한 모 든 구조들을 초구조로 경제성 평가 모델을 기준으로 평가되었다. 본 연구는 2014년도 정부(미래창조과학부)의 재원으로 (재)한국이산화탄소포집 및 처리연구개발센터의 지원을 받아 수행된 연구임(2014M1A8A1049305).

Most real world design evaluation and risk-based decision support combine quantitative and qualitative (linguistic) variables. Decision making based on conventional mathematics that combines qualitative and quantitative concepts always exhibit difficulty in modelling actual problems. The successful selection process for choosing a design/procurement proposal is based on a high degree of technical integrity, safety levels and low costs in construction, corrective measures, maintenance, operation, inspection and preventive measures. In this paper, a design decision support framework using a composite structure methodology grounded in approximate reasoning approach and evidential reasoning method is suggested for design evaluation of machinery space of a ship engine room at the initial stages. An illustrative example is used to demonstrate the application of the proposed framework.

To ensure the successful launch of the Korea pathfinder lunar orbiter (KPLO) mission, the Korea Aerospace Research Institute (KARI) is now performing extensive trajectory design and analysis studies. From the trajectory design perspective, it is crucial to prepare contingency trajectory options for the failure of the first lunar brake or the failure of the first lunar orbit insertion (LOI) maneuver. As part of the early phase trajectory design and analysis activities, the required time of flight (TOF) and associated delta-V magnitudes for each recovery maneuver (RM) to recover the KPLO mission trajectory are analyzed. There are two typical trajectory recovery options, direct recovery and low energy recovery. The current work is focused on the direct recovery option. Results indicate that a quicker execution of the first RM after the failure of the first LOI plays a significant role in saving the magnitudes of the RMs. Under the conditions of the extremely tight delta-V budget that is currently allocated for the KPLO mission, it is found that the recovery of the KPLO without altering the originally planned mission orbit (a 100 km circular orbit) cannot be achieved via direct recovery options. However, feasible recovery options are suggested within the boundaries of the currently planned delta-V budget. By changing the shape and orientation of the recovered final mission orbit, it is expected that the KPLO mission may partially pursue its scientific mission after successful recovery, though it will be limited.