본 논문에서는 고준위폐기물 처분용기를 지하 심지층에 처분하기 위하여 요구되는 구조설계 요구조건과 구조안전성 평가 기준을 도출하였다. 고준위폐기물은 높은 열과 많은 방사능을 방출하기 때문에 고준위폐기물을 넣어 보관하는 처분용기는 그 취급에 많은 주의가 요구된다. 이를 위하여 고준위폐기물 처분용기는 장기간(보통 10,000년 동안) 안전한 장소에 보관되어야 한다. 보통 이 보관 장소는 지하 500m에 위치한다. 지하 깊은 화강암에 고준위폐기물을 보관하도록 설계되는 처분용기는 내부주철삽입물과 이를 감싸고 있는 부식에 강한 와곽쉘, 위 덮개와 아래 덮개로 구성되는 구조로 되어 있으며 지하수압과 벤토나이트 버퍼의 팽윤압을 받는다. 따라서 고준위폐기물 처분용기는 심지층에 보관 시 이들 외력들을 견디도록 설계되어야 한다. 만약에 발생 가능한 모든 하중조합을 고려한 처분용기 설계가 되지 않으면 심지층에 위험한 고준위폐기물 처분 시에 처분용기에 소성변형이나 크랙 또 좌굴같은 구조적 결함이 발생할 수 있다. 따라서 심지층에 처분용기를 처분 시에 처분용기에 발생하는 구조적 문제들이 발생하지 않게 하기 위하여 여러 가지 구조해석이 수행되어야 한다. 이러한 구조해석 수행에 앞서 처분용기 설계 타당성을 평가하기 위한 기준이 필요하다. 또한 평가기준에 영향을 미치는 설계요구조건(설계변수)이 명확히 검토되어야 한다. 따라서 본 논문에서는 처분용기의 구조설계 요구조건(설계변수)과 구조 안전성 평가기준을 도출하고자 한다.

Autocrine or paracrine mediators released by the early embryo are implicated in the support of embryonic development. Their mechanisms and optimal embryo density in the medium, however, are uncertain. This study was conducted to establish the optimal embryo density and culture medium volume in mouse parthenogenetic embryo culture. In experiment 1, culture of parthenogenetirally activated oocytes at a concentration of 2~4 embryos/ uL significantly improved development to the blastoryst stage (72%≤) compared with culture at the lower (0.2~1 embryos㎕, 0~37.5%) and the higher (5~6 embryos㎕, 30~53%) concentration for 120 h when the oocytes were cultured in a 5㎕ drop under mineral oil In experiment 2, the embryos cultured at a concentration of 2~4 embryos㎕ in a 10㎕ drop (81.1%) showed significantly higher blastocyst rates than those in a 5㎕ drop (68.5%). This study optimizes in vitro culture condition by modifying embryo density and the volume of culture medium It may give appropriate level of autocrine and/or paracrine factors to enhance viability and subsequent normal development of mouse parthenogenetic embryos in vitro.

This paper analyzes delta-Vs to maintain an extremely low altitude on the Moon and investigates the possibilities of performing a CubeSat mission. To formulate the station-keeping (SK) problem at an extremely low altitude, current work has utilized real-flight performance proven software, the Systems Tool Kit Astrogator by Analytical Graphics Inc. With a high-fidelity force model, properties of SK maneuver delta-Vs to maintain an extremely low altitude are successfully derived with respect to different sets of reference orbits; of different altitudes as well as deadband limits. The effect of the degree and order selection of lunar gravitational harmonics on the overall SK maneuver strategy is also analyzed. Based on the derived SK maneuver delta-V costs, the possibilities of performing a CubeSat mission are analyzed with the expected mission lifetime by applying the current flight-proven miniaturized propulsion system performances. Moreover, the lunar surface coverage as well as the orbital characteristics of a candidate reference orbit are discussed. As a result, it is concluded that an approximately 15-kg class CubeSat could maintain an orbit (30–50 km reference altitude having ±10 km deadband limits) around the Moon for 1–6 months and provide almost full coverage of the lunar surface.

In spite of a short history of only 30 years in space development, Korea has achieved outstanding space development capabilities, and became the 11th member of the “Space Club” in 2013 by launching its own satellites with its own launch vehicle from a local space center. With the successful development and operation of more than 10 earth-orbiting satellites since 1999, Korea is now rapidly expanding its own aspirations to outer space exploration. Unlike earth-orbiting missions, planetary missions are more demanding of well-rounded technological capabilities, specifically trajectory design, analysis, and navigation. Because of the importance of relevant technologies, the Korean astronautical society devoted significant efforts to secure these basic technologies from the early 2000s. This paper revisits the numerous efforts conducted to date, specifically regarding flight dynamics and navigation technology, to prepare for future upcoming planetary missions in Korea. However, sustained efforts are still required to realize such challenging planetary missions, and efforts to date will significantly advance the relevant Korean technological capabilities.