• Aerospace Engineering and Technology
• /
• v.5 no.2
• /
• pp.143-148
• /
• 2006

This article summarizes the results of sea transportation load measurements, which will be used as the reference to the sea transportation environment condition for the launch vehicle of KSLV-I. KSLV-I will be transported by Sea from Pusan to the NARO space center in Gohung, Chunnam province. Since the vibration load condition during sea transportation is considered as one of the important design parameters of KSLV-I and its transportation means, it is necessary to directly measure the environmental condition of sea transportation loads prior to establish the sea transportation plan in detail. This material includes the measured data of 3-axis linear accelerations and 3-axis angular rates on the board of a barge-ship, which is towed by a tug boat during shipping operation. This barge-ship is same class with one which will actually carry KSLV-I. The results show that the measured load condition during sea transportation is not severer than the reference data of MIL-STD-810F and Zenit-3SL launch system.

• Aerospace Engineering and Technology
• /
• v.9 no.1
• /
• pp.116-124
• /
• 2010

Ground complex composed of Assembly Complex(AC) and Launch Complex(LC) which is located on Oenarodo space center in Kohung is necessary for successful launching of KSLV-I. AC performs accepting of a KSLV-I 1st stage and 2nd stage, stage assembly, the integrated launch vehicle, the checked out, and all kinds of performance test, pre-launch tests and processing. At AC, the mechanical support equipments, that is called the technological equipments, are installed in the Launch Vehicle Assembly Test Building(LVATB). These technological equipments have diverse forms of an interface with mechanical/electric device of the launch vehicle and have to provide a condition and the performance guarantee of an optimum in the launching operation process. In this paper, the requirements specification and manufacturing performance test for the mechanical support equipments which are used in the assembly/disassembly and test of the launch vehicle are introduced.

• Aerospace Engineering and Technology
• /
• v.9 no.1
• /
• pp.60-66
• /
• 2010

This paper deals with a post-processing of GPS receiver data in order to acquire a reference flight trajectory of an aircraft test. The flight test using an aircraft that is carried out several times since 2007 is the integrated test to verify the performance of the tracking and communications facilities in Naro Space Center and Jeju Tracking Center. In order to analyze performance of the tracking and navigation equipments, true reference data should be used for performance comparisons. Therefore off-the-shelf commercial GPS receiver, DL-V3 made by NovAtel Inc., is operated on the test to collect the GPS navigation data and the collected data is post-processed by GrafNav which is the off-the-shelf post-processing program made by NovAtel Inc. Through the post-processing of the collected data, a reference trajectory is generated with small error range about several decade centimeter level.

• Aerospace Engineering and Technology
• /
• v.7 no.1
• /
• pp.229-235
• /
• 2008

The ground flight termination system(GFTS) could be used for the termination of launch vehicle in flight motion when the launch vehicle deviates from the designated route due to the system malfunction or failure as well as the launch vehicle can't be tracked by the ground tracking system. This paper introduces the basic concept and design of the ground flight termination system to be used for KSLV launch mission in NARO space center. In order to design the optimal ground flight termination system for KSLV launch application, the operational concept reflected on the flight trajectory and system characteristics of KSLV launch vehicle should be considered. Moreover the RF link budget analysis, and the analysis for system availability and reliability are done. Based on the analysis above, the each subsystem of ground flight termination to transmit the termination signal in stable is designed for KSLV launch mission.

• Journal of Astronomy and Space Sciences
• /
• v.23 no.4
• /
• pp.355-372
• /
• 2006

Mission opportunities and trajectory characteristics for the future Korean Mars mission have designed and analyzed using KSIV-III(Korea Space Launch Vehicle-III). Korea's first space center, 'NARO space center' is selected as a launch site. For launch opportunities, year 2033 is investigated under considering the date of space center's completion with KSLV series development status. Optimal magnitude of various maneuvers, Trans Mars Injection (TMI) maneuver, Trajectory Correction Maneuver (TCM), Mars Orbit Insertion (MOI) maneuver and Orbit Trim Maneuver(OTM), which are required during the every Mars mission phases are computed with the formulation of nonlinear optimization problems using NPSOL software. Finally, mass budgets for upper stage (launcher for KSIV-III and spacecraft are derived using various optimized maneuver magnitudes. For results, daily launch window from NARO space center for successful Korean Mars mission is avaliable for next 27 minutes starting from Apr. 16. 2033. 12:17:26 (UTC). Maximum spacecraft gross mass which can delivered to Mars is about 206kg, with propellant mass of 109kg and structure mass of 97kg, when on board spacecraft thruster's Isp is assumed to have 290 sec. For upper stage, having structure ratio of 0.15 and Isp value of 280 sec, gross mass is about 1293kg with propellant mass of 1099kg and structure mass of 194kg. However, including 10% margins to computed optimal maneuver values, spacecraft gross mass is reduced to about 148kg with upper stage's mass of 1352kg. This work will give various insights, requiring performances to developing of KSIV-III and spacecraft design for future Korean Mars missions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1180-1183
• /
• 2017

The Propulsion System Test Complex (PSTC) is constructed for developing KSLV-II in the Naro space center. The KSLV-II uses LOX for oxidizer and oxidizer filling algorithm is developed for supplying oxidizer to KSLV-II. This paper introduces oxidizer filling algorithm.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.10 no.1
• /
• pp.45-56
• /
• 2002

This study is performed to analyze the turbulence effect by the analysis of the parameters related with flight data of FDR(Flight Data Recorder). In the analysis, the SSFDR(Solid State Flight Data Recorder) flight data of B747-400 and B767-300 model aircraft was selected. Through this study, we verified that turbulence interfere with flight safety because it is modifiable to flight situation and condition of aircraft.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.162.1-162.1
• /
• 2012

한국형 달 착륙선의 안전하고 효율적인 달 착륙을 위해 임무 시나리오 시뮬레이션을 수행하였다. 달 착륙은 보통 두 가지 방법이 사용되는데, 지구에서 출발하여 달에 도착한 후 달착륙지에 직접 착륙하는 방법과 달의 주차궤도를 돌다가 달 착륙지에 착륙하는 방법이 있다. 미국의 Surveyor호는 직접 착륙 방법을 사용하였고 아폴로 시리즈는 달 궤도를 공전하다가 착륙하는 방법을 사용하였다. 본 연구에서는 두 가지 방법을 모두 사용하여 착륙 임무 시나리오를 시뮬레이션을 수행한 후 장단점을 비교분석하였다. 달 주차궤도를 이용한 착륙은 달고도 100km에서 공전을 하다가 고도 15km까지 하강한 후 Powered descent 단계를 통해 착륙지에 착륙하는데 Powered descent 단계는 다시 감속단계, 접근 단계, 최종 하강 단계로 나뉘어진다. 달 착륙선은 나로우주센터에서 KSLV-2에 실려 2025년에 발사되며, 달 착륙지는 달의 과학적 임무를 고려하여 달 남극 근처로 가정하였다. 달 착륙 시뮬레이션을 통해 달 착륙선의 비행 궤적과 필요한 연료량 계산 등의 정보를 통해 직접 착륙 방법과 달 주차궤도를 이용하는 방법의 장단점을 확인할 수 있었다.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
• /
• 2012.04a
• /
• pp.381-384
• /
• 2012

2010년 06월 09일 소형위성발사체의 비행시험을 준비 하던 중 화재확산방지 장치가 오작동 하는 사고가 발생 하였다. 이 사고로 소화수 100톤과 소화약제 3톤이 분출 되었고, 소형위성발사체의 비행시험은 하루 지연 되었다. 오작동의 직접적 원인은 제어기 부분의 오작동으로 판단되어, 관련 제어기 및 통신라인 부품들을 모두 교체하고, 발사통제동과 발사대간의 통신선로도 이중화 하였다. 아울러 제어기의 입출력 신호를 실시간으로 기록하기 위한 장비도 추가로 설치하여 전반적인 설비의 신뢰도를 높였다.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2011.08a
• /
• pp.143-143
• /
• 2011

발표자는 본 발표를 통해 현재 표준연구원에서 진행되고 있는 플라즈마 연구들 간단히 소개하는 시간을 가질까 한다. 표준연구원/진공센터내의 플라즈마팀은 진공기반구축사업,반도체진공공정실시간측정기술개발 사업등의 후원을 받아 지난 10년각 국내 최대의 플라즈마 연구 인프라를 갖추는데 성공하였으며 이를 바탕으로 해외 우주기관과 견줄만한 플라즈마 발생장치, 진단장치, 전산모사시스템 등을 확보한 상태이다. 본발표를 통해 그간 표준연구원에서 진행하고 있는 플라즈마 진단시스템, 모니터링 시스템, 플라즈마원개발, 시뮬레이션 연구, 공정해석 연구등을 간략하게 소개드릴려고 한다.