• Title/Summary/Keyword: 초기 발사단계

Search Result 47, Processing Time 0.021 seconds

Persistent Scatterer Selection and Network Analysis for X-band PSInSAR (X-band PSInSAR를 위한 고정산란체 추출 및 네트워크 분석 기법)

  • Kim, Sang-Wan;Cho, Min-Ji
    • Korean Journal of Remote Sensing
    • /
    • v.27 no.5
    • /
    • pp.521-534
    • /
    • 2011
  • The high-resolution X-band SAR systems such as COSMO-SkyMED and TerraSAR-X have been launched recently. In addition KOMPSAT-5 will be launched in the early of 2012. In this study we developed the new method for persistent scatterer candidate (PSC) selection and network construction, which is more suitable for PSInSAR analysis using multi-temporal X-band SAR data. PSC selection consists in two main steps: first, selection of initial PSCs based on amplitude dispersion index, mean amplitude, mean coherence. second, selection of final PSCs based on temporal coherence directly estimated from network analysis of initial PSCs. To increase the stability of network the Multi- TIN and complex network for non-urban area were addressed as well. The proposed algorithm was applied to twenty-one TerraSAR-X SAR of New Orleans. As a result many PSs were successfully extracted even in non-urban area. This research can be used as the practical application of KOMPSAT-5 for surface displacement monitoring using X-band PSInSAR.

Solar Array Deployment Analysis of a Satellite (인공위성 태양전지판 전개해석)

  • Kim, Kyung-Won;Kim, Sun-Won;Lim, Jae-Hyuk;Rhee, Ju-Hun;Hwang, Do-Soon;Jin, Ik-Min;Kim, Hak-Jung;Song, Woon-Hyung;Choi, Hang-Suk
    • Journal of Satellite, Information and Communications
    • /
    • v.3 no.1
    • /
    • pp.29-34
    • /
    • 2008
  • After spacecraft is separated from the launch vehicle, first of all spacecraft deploy the solar array. Solar array deployment is one of the key factors deciding the success of the spacecraft mission. Therefore, It is necessary to predict the solar array deployment motion and check the safety through calculating the load on the tape hinges of solar array using the deployment analysis in the initial design phase. In this paper, solar array deployment analysis is performed by multi-body dynamics simulation program. From the analysis results, assessment on the safety also is carried out. In addition, hinge characteristic test is fulfilled to find out hinge characteristic, and is applied to the deployment analysis.

  • PDF

Validation on Solar-array Drive Assembly of GEO-KOMPSAT-2A Through In-orbit Operation (천리안2A호 태양전지판구동기 궤도상 운영 검증)

  • Park, Young-Woong;Park, Keunjoo;Park, Bong-Kyu
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.47 no.4
    • /
    • pp.283-288
    • /
    • 2019
  • In this paper, there is summarized the validation of ground test results through the telemetry acquired during on-orbit initial activation on solar-array drive assembly(SDA) of GK2A launched at Dec-5, 2018. Especially, the decision logic of SDA initial position and the compensation logic are validated and confirmed. The SDA initial position is needed when GK2A enter to geostationary orbit from transfer orbit and the compensation logic is for the accumulated position error due to the open-loop control. Up to now, it is normal operating. Also the periodic offset between the geostationary orbit and Sun position is found that it is not checked on design phase, and then the proper threshold value is applied.

Scenario Design for Verification of Rendezvous Docking Technology for Nanosatellite (초소형 위성의 랑데부/도킹 기술 검증을 위한 시나리오 설계)

  • Kim, Kiduck;Kim, Hae-Dong;Cho, Dong-Hyun
    • Journal of Space Technology and Applications
    • /
    • v.2 no.1
    • /
    • pp.30-40
    • /
    • 2022
  • This paper illustrates the trajectory design of drift distance recovery after initial launch and proximity operation when verifying rendezvous/docking technology using nanosatellites. The rendezvous/docking is a technology that is the basis of on-orbit servicing technology and is a preemptive process essential for approaching a target object. In particular, since it is difficult to verify in space, nanosatellites have recently been used to reduce the risk and cost of the development stage. Therefore, this paper not only introduces the configuration and specifications of thrusters for nanosatellites but also designs relative trajectories that can take into account the thrust limitations which come from the small size and low power of nanosatellites. In addition, we intend to be helpful in later designing scenarios according to the improvement of available thruster performance through comparison of trajectories and thrust usage with cases without thrust limitations.

Research for Space Activities of Korea Air Force - Political and Legal Perspective (우리나라 공군의 우주력 건설을 위한 정책적.법적고찰)

  • Shin, Sung-Hwan
    • The Korean Journal of Air & Space Law and Policy
    • /
    • v.18
    • /
    • pp.135-183
    • /
    • 2003
  • Aerospace force is a determining factor in a modem war. The combat field is expanding to space. Thus, the legitimacy of establishing aerospace force is no longer an debating issue, but "how should we establish aerospace force" has become an issue to the military. The standard limiting on the military use of space should be non-aggressive use as asserted by the U.S., rather than non-military use as asserted by the former Soviet Union. The former Soviet Union's argument is not even strongly supported by the current Russia government, and realistically is hard to be applied. Thus, the multi-purpose satellite used for military surveillance or a commercial satellite employed for military communication are allowed under the U.S. principle of peaceful use of space. In this regard, Air Force may be free to develop a military surveillance satellite and a communication satellite with civilian research institute. Although MTCR, entered into with the U.S., restricts the development of space-launching vehicle for the export purpose, the development of space-launching vehicle by the Korea Air Force or Korea Aerospace Research Institute is beyond the scope of application of MTCR, and Air Force may just operate a satellite in the orbit for the military purpose. The primary task for multi-purpose satellite is a remote sensing; SAR sensor with high resolution is mainly employed for military use. Therefore, a system that enables Air Force, the Korea Aerospace Research Institute, and Agency for Defense Development to conduct joint-research and development should be instituted. U.S. Air Force has dismantled its own space-launching vehicle step by step, and, instead, has increased using private space launching vehicle. In addition, Military communication has been operated separately from civil communication services or broadcasting services due to the special circumstances unique to the military setting. However, joint-operation of communication facility by the military and civil users is preferred because this reduces financial burden resulting from separate operation of military satellite. During the Gulf War, U.S. armed forces employed commercial satellites for its military communication. Korea's participation in space technology research is a little bit behind in time, considering its economic scale. In terms of budget, Korea is to spend 5 trillion won for 15 years for the space activities. However, Japan has 2 trillion won annul budget for the same activities. Because the development of space industry during initial fostering period does not apply to profit-making business, government supports are inevitable. All space development programs of other foreign countries are entirely supported by each government, and, only recently, private industry started participating in limited area such as a communication satellite and broadcasting satellite, Particularly, Korea's space industry is in an infant stage, which largely demands government supports. Government support should be in the form of investment or financial contribution, rather than in the form of loan or borrowing. Compared to other advanced countries in space industry, Korea needs more budget and professional research staff. Naturally, for the efficient and systemic space development and for the prevention of overlapping and distraction of power, it is necessary to enact space-related statutes, which would provide dear vision for the Korea space development. Furthermore, the fact that a variety of departments are running their own space development program requires a centralized and single space-industry development system. Prior to discussing how to coordinate or integrate space programs between Agency for Defense Development and the Korea Aerospace Research Institute, it is a prerequisite to establish, namely, "Space Operations Center"in the Air Force, which would determine policy and strategy in operating space forces. For the establishment of "Space Operations Center," policy determinations by the Ministry of National Defense and the Joint Chief of Staff are required. Especially, space surveillance system through using a military surveillance satellite and communication satellite, which would lay foundation for independent defense, shall be established with reference to Japan's space force plan. In order to resolve issues related to MTCR, Air Force would use space-launching vehicle of the Korea Aerospace Research Institute. Moreover, defense budge should be appropriated for using multi-purpose satellite and communication satellite. The Ministry of National Defense needs to appropriate 2.5 trillion won budget for space operations, which amounts to Japan's surveillance satellite operating budges.

  • PDF

In Vivo Study on the Biocompatibility of New Resin-based Root Canal Sealers (신개발 레진 계열 봉함제의 생체친화성에 관한 연구)

  • Kim, Yong-Beom;Baek, Seung-Ho;Bae, Kwang-Shik
    • Restorative Dentistry and Endodontics
    • /
    • v.27 no.2
    • /
    • pp.122-134
    • /
    • 2002
  • 목적 : 근관 치료의 최종 목적인 근관계의 영구적인 충전을 위해 사용되는 근관 봉함제는 많은 연구와 개선을 거쳐서 현재는 다양한 성분의 봉함제가 시판되고 있다. 이중에서 레진이 주성분인 봉함제는 조작이 편리하고 흐름성이 좋으며 근관의 벽에 높은 밀폐성을 보이고 충분한 작업시간과 높은 방사선 불투과성을 가지는 장점을 가짐에도 불구하고 높은 초기 생체 독성을 나타내는 단점을 가지고 있다. 본 실험에서는 기존의 상용화된 제품 중 레진이 주성분인 두 종류의 봉함제(AH 26, AH plus)와 산화아연이 주성분인 봉함제(Pulp Canal Sealer EWT)와 국내에서 새로이 개발한 제품으로서 레진이 주성분인 두 종류의 봉함제(Adseal-1,2)를 생체조직에 매식하여 국소적인 반응을 비교하여 생체친화성을 알아보고자 하였다. 방법 : 수종 봉함제의 생체 친화성을 알아보기 위하여 64마리의 Sprague-Dawley rat을 사용하였다. 봉함제의 피하조직 매식을 위해 길이와 직경이 각각 5와 1.5mm인 폴리에틸렌 테프론 관을 사용하였으며 이를 에탄올과 증류수로 세척 한 후 고압증기멸균을 시행하였다. Rat에 대하여 케타민으로 복강내 마취를 시행한 후 배부를 면도하고 iodine으로 소독한 다음 네 곳에 절개를 시행하였으며 blunt dissection을 통해 깊이 10mm이상의 피하조직 pocket을 형성하였다. 각각의 봉함제를 제조사의 지시 에 따라 혼합 후 즉시 멸균된 테프론 관에 주사기를 이용하여 담은 다음에 봉함제가 흐르지 않게 유의하며 pocket내로 삽입하였으며 이때 16개의 관을 대조군으로 사용하기 위해 봉함제를 넣지 않은 상태로 삽입하였다. 이 후 절개 부위를 surgical gut suture로 봉합하였으며 1주일 후에 발사하였다. Rat을 1, 2, 4, 12주 후에 각 군 당 세 마리 씩 에테르 흡입을 통해 희생하였으며 이 때 한 마리씩의 대조군도 포함시켰다. 이 후 매식된 관을 주위 조직과 함께 제거하고 포르말린에서 48시간 고정시킨 후 파라핀에 포매한 다음에 micro-tome을 사용하여 6$\mu\textrm{m}$로 serial section을 시행하였다. 정중선 부위의 시편에 Hematoxylin-Eosin staining을 시행한 후 Olsson, Orstavik 그리고 Mjor 등의 방법에 따라 조직학적 변화를 관찰한 후 slight(1), moderate(2), severe inflammation(3)의 단계로 분류하였다. 얻어진 결과를 통계처리 프로그램인 Jandel사의 Sigmastat을 이용하여 Kruskal Wallis Test로 통계처리를 하였다. 결과 : (Table omitted) 결론 : 1) Pulp Canal Sealer를 제외한 모든 군에서 시간이 지남에 따라 유의성 있게 염증이 감소되는 양상을 보였다(p<0.05). 2) Pulp Canal Sealer는 1주, 2주, 12주에서 강한 염증반응을 보였다. 3) AH 26과 AH Plus에서는 1주, 2주에서 강한 염증반응을 보였으나 12주에서는 염증반응이 감소하였다. 4) 새로 개발된 봉함제 Adseal-1,2는 1주, 2주에서는 가장 약한 염증반응을 보이나 4주, 12주 후에는 AH Plus와 비슷한 수준의 염증 반응을 보였다. 5) Pulp Canal Sealer를 제외한 모든 군에서 인정할 만한 생체친화성을 보였다. 6) Adseal-2가 Adseal-1에 비하여 전반적으로 낮은 염증반응을 보였다. 7) 각 군간 결과의 차이에 통계적 유의성은 없었다(p>0.05).

A Study on the Design and Rectification Method of a KW class Power Converter Unit for an Aircraft Mounted Guided Missile (항공기 장착 유도탄의 KW급 전력변환장치 설계와 정류방식에 따른 연구)

  • Kim, Hyung-Jae;Jung, Jae-Won;Lee, Dong-Hyeon;Kim, Gil-Hoon;Moon, Mi-Youn
    • Journal of Advanced Navigation Technology
    • /
    • v.26 no.2
    • /
    • pp.99-104
    • /
    • 2022
  • Recently, the domestic demand for weapon systems based on aircraft platforms is gradually increasing. In particular, the demand for effective precision guided missile(PGM) which cruises for several hundred kilometers after launch to strike the ground target is rising drastically, but it is in the early stages of development, and research based on it are limited. This paper is a study on the power converter unit(PCU) within PGM which is mounted on an aircraft platform based on MIL-STD-1760, which is an interface between an aircraft and PGM. We investigated the electrical properties and structure of the umbilical connector, and the aircraft/store electrical interconnection system. Also, the focus on the design specifications of the PCU that supplies power were described. This result 3 phase AC input, which is the state for the guided simulation power supply in the state of being mounted on an aircraft that rectification method with power factor correction(PFC) compared to bridge rectifier circuit. In the future, it may be used as a basis for power supply design on aircraft mounted weapon systems.