• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.96-102
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• 2012

Recently, interests about frame error reduction method, using multiple PCM data which are received at several ground stations, are increasing. Simple data merge method is already applied to data processing system at Naro Space Center and have been used in the first and the second flight test analysis of KSLV-I. This paper is focused on error reduction with error correcting merge algorithm and time-delayed data correction algorithm. Result of applying the proposed algorithms to the flight test data shows 1.32% improvement in error rate, compared to simple-data-merge method. It is considered that presented algorithms could be very useful in generating various telemetry merge data.

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.1
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• pp.86-95
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• 2010

Flight termination system(FTS) is used to terminate safely the launch vehicle's flight when it faces an emergency situation by transmitting termination command from ground FTS. RCC standard IRIG tone method has been used widely for FTS commands method in foreign ranges and Naro Space Center, but this method has a weakness for security of command signal. Therefore RCC had studied more secured EFTS standard and chose CPFSK digital modulation method. This paper describes basic concept and types of FTS and FTS types which foreign ranges had applied and describes standardization of EFTS in the U.S. based on RCC EFTS study reports.

• Journal of Korean Society for Quality Management
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• v.47 no.3
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• pp.401-415
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• 2019

Purpose: When the SURION Aircraft operated in the fields, cracks are found in PU(polyurethane) Strip on main rotor blade. This study has been conducted to explain PU(polyurethane) Strip crack phenomenon of SURION main rotor blade and to propose useful solution of it by experimental method. Methods: This study considered a lot of factor because the SURION is operated at severe environment. This study investigated the influence of temperature, thermal shock, paint and primer process, PU Strip material, primer material. Results: The results of this study are as follows; The primer process was most excellent influence. The Application of primer having a brittleness caused by a crack of PU Strip. Other factors have influenced on the PU Strip, but they can not be controlled because they are related to the SURION's operating environment. Conclusion: The Quality of PU Strip on SURION main rotor blade was improved through removing the primer process. Finally, the reliability of main rotor blade was guaranteed through improving the quality of PU Strip.

• The Korean Journal of Air & Space Law and Policy
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• v.26 no.1
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• pp.177-213
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• 2011

The purpose of this paper is to research on the liability and cases for space damage with reference to the space activity under the international space treaty and national space law of major countries. The United Nations has adopted two treaties relating to the liability for space damage as follows: the Outer Space Treaty of 1967 and the Liability Convention of 1972. Korea has enacted the Outer Space Damage Compensation Act of 2008 relating to the liability for space damages. The Outer Space Treaty of 1967 regulates the international responsibility for national activities in outer space, and the national tort liability for damage by space launching object. The Liability Convention of 1972 regulates the absolute liability by a launching state, the faulty liability by a launching state, the joint and several liability by a launching state, the person claiming for compensation, the claim method for compensation, the claim period of compensation, the claim for compensation and local remedy, the compensation amount for damage by a launching state, and the establishment of the Claims Commission. The Outer Space Damage Compensation Act of 2008 in Korea regulates the definition of space damage, the relation of the Outer Space Damage Compensation Act and the international treaty, the non-faulty liability for damage by a launching person, the concentration of liability and recourse by a launching person, the exclusion of application of the Product Liability Act, the limit amount of the liability for damage by a launching person, the cover of the liability insurance by a launching person, the measures and assistance by the government in case of occurring the space damage, and the exercise period of the claim right of compensation for damage. There are several cases with reference to the liability for damage caused by space accidents as follows: the Collision between Iridium 33 and Cosmos 2251, the Disintegration of Cosmos 954 over Canadian Territory, the Failure of Satellite Launching by Martin Marietta, and the Malfunctioning of Westar VI Satellite. In the disputes and lawsuits due to such space accidents, the problems relating to the liability for space damage have been settled by the application of absolute(strict) liability principle or faulty liability principle. The Liability Convention of 1972 should be improved as follows: the clear definition in respect of the claimer of compensation for damage, the measure in respect of the enforcement of decision by the Claims Commission. The Outer Space Damage Compensation Act of 2008 in Korea should be improved as follows: the inclusion of indirect damage into the definition of space damage, the change of the currency unit of the limit amount of liability for damage, the establishment of joint and several liability and recourse right for damage by space joint launching person, and the establishment of the Space Damage Compensation Review Commission. Korea has built the space center at Oinarodo, Goheung Province in June 2009. Korea has launched the first small launch vehicle KSLV-1 at the Naro Space Center in August 2009 and June 2010. In Korea, it will be the possibility to be occurred the problems relating to the international responsibility and the liability for space damage in the course of space activity. Accordingly the Korean government and launching organization should make the legal and systematic policy to cope with such problems.

• Journal of Astronomy and Space Sciences
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• v.22 no.4
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• pp.501-512
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• 2005

This research supposed when a fictitious KSIV-I space launch vehicle launches from NARO space center. This compared and analyzed the results from real-time trajectory estimation using the Extended Kalman Filter and the Unscented Kalman Filter. A virtual trajectory and observation data are generated for the fictitious KSLV-I and three measurement radars. The performances of both Otters are compared for several simulations with small initial errors, large initial errors, 20Hz and 10Hz data rate. The results show that the Unscented Kalman Filter yields faster convergence and more accurate than the Extended Kalman Filter for the cases with larger initial error and slower data rate conditions.

• Journal of the Korean Geotechnical Society
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• v.37 no.2
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• pp.5-17
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• 2021

The Moon has been an attractive planet as an outpost for deep space exploration since He-3 and water ice which can be used as energy resources were discovered. In-Situ Resource Utilization (ISRU) construction material fabrication method is required for sustainable space planet exploration. In this paper, the possibility of microwave sintering technology for construction material fabrication was evaluated using lunar regolith that can be easily collected from the Moon surface. Experimental assessment of the influence factors on microwave sintering was conducted using a hybrid sintering system for efficient processing. The heat distribution in the furnace was observed using thermal paper that is coated with a material formulated to change color when exposed to heat. Based on this result, sintered cylindrical KLS-1s with a diameter of 1 cm and a height of 2 cm were fabricated. Densities were measured for the sintered KLS-1s under rotating turntable conditions that have an effect of microwave dispersion. The more dielectrics were arranged, the more microwaves were dispersed reducing the heat concentration, and thus a uniformity of sintered KLS-1s was enhanced.

• The Bulletin of The Korean Astronomical Society
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• v.42 no.1
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• pp.35.2-35.2
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• 2017

국립고흥청소년우주체험센터는 덕흥천문대 1M망원경으로 관측한 자료를 축적하고 있다. 1M망원경이 설치 된 후 발생했던 문제점인 광축, 극축, 지향정밀도, 추적정밀도를 개선하기 위해 시도했던 방법의 결과를 개선 전후 관측 자료를 비교하여 소개하고자 한다. 현재는 오토가이드 없이 별 추적이 3600초 정도 가능하다. 또한, 스크립트 활용으로 소프트웨어를 개선하여 관측의 용이성을 증대시켰다. 은하측광, 분광, 시계열관측 등 차별화된 연구를 수행하기 위한 기기 및 소프트웨어의 확충 보완을 수행하고 있다.

• Korean Chemical Engineering Research
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• v.61 no.2
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• pp.208-216
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• 2023

In this study, using the Delphi method, 20 responses to 4 questions (need for launch safety control, top-priority considerations for ensuring public safety during launch, necessary improvements for securing maritime safety, and maritime safety threat factors) regarding launch vehicles and public safety were obtained from experts, and their importance was evaluated to analyze the factors that threaten the reinforcement of maritime safety around launch sites and flight paths when launching. According to the results of an analytic hierarchy process (AHP) analysis, the consistency ratio of the four questions was 4.8%, which is lower than CR ≤ 0.1(10%), and the consistency percentage of the lower measurement indicators was 3.9~5.7%. The derived importance and priority of maritime safety threat factors during launching were in the following order: Substantial human and physical damage in case of launch accidents(0.36), Prepare legal bases (e.g., penalty details) regarding maritime control(0.32), Secure the safety of personnel, equipment, and facilities in danger zone(0.31), Unauthorized entry of vessels in maritime control zones and non-compliance to restrictions(0.30). This article can serve as a reference for strengthening maritime safety in areas around launch sites and flight paths.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.10
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• pp.881-891
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• 2017

In this paper, we described the new TLE(Two Line Elements) generation method based on the compansation technique by using past TLEs(Two Line Elements) released by JSpOC(Joint Space Operation Center) in USA to reduce the orbit prediction error for long duration of SGP4(Simplified General Perturbations 4) which is a simplifed and analytical orbit propagator. The orbital residuals the orbital difference between two ephemeris for the first TLE only and for the all TLEs updated by JSpOC for the past some period was applied for this algorithm instead of general orbit determination software. Actually, in these orbital residuals, the trend of orbit prediction error from SGP4 is included. Thus, it is possible to make a simple residual function from these orbital residulas by using the fitting process. By using these residual functions with SGP4 prediction data for the currnet TLE data, the compansated orbit prediction can be reconstructed and the orbit prediction error for long duration of SGP4 is also reduced. And it is possible to generate new TLE data from it. In this paper, we demonstraed this algorithm in simple simulation, and the orbital error is decreased dramatically from 4km for the SGP4 propagation to 2km for it during 7 days as a result.

• Journal of the Korean Society of Industry Convergence
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• v.27 no.1
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• pp.207-212
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• 2024

Recently, with the strengthening of environmental regulations, there has been an increasing interest in eco-friendly energy sources, leading to a trend of the increasing scale of Cargo Containment Systems (CCS) for Liquefied Natural Gas (LNG) carriers. Among these systems, membrane tanks have gained popularity in LNG transport vessels due to their superior spatial utilization and competitiveness. However, due to high initial investment costs and the difficulty in repair in case of damage, a safety layer, the secondary barrier, must be installed without fail. In this study, in order to apply a new secondary barrier to the existing membrane-type LNG CCS, tests were conducted on the fiberglass layer previously used in the Triplex-Flexible Secondary Barrier (FSB), substituting it with basalt fiber. Tensile and vertical tensile tests were performed to assess the newly applied material. Environmental tests were conducted at room temperature (25℃) and extremely low temperatures (-170℃), considering the temperatures to which substances may be exposed during LNG vessel operations. The basalt-FSB produced in this study demonstrated superior results compared to the specifications of the existing product, confirming its potential applicability for implementation.