• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.106-113
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• 2002

In spacecraft system, structure subsystem has the mission of supporting all the components safely under various space environmental conditions. The safety of spacecraft structure is finally verified from the coupled load analysis, which is a branch of load analysis which combines the launch vehicle and satellite. This study introduces the optimization algorithm to reduce the weight of spacecraft structure under launch environmental conditions directly. The acceleration responses are obtained by the introduction of coupled load analysis, which lead to check the failure of spacecraft structural members. The results show a 12% saving of structural weight and this saving is mainly driven by the thickness of honeycomb core, which strongly affects the natural frequencies of platforms and panels.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.6
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• pp.457-464
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• 2021

To analyze the buffet phenomenon that causes serious vibration loads on a satellite launch vehicle, the pressure fluctuations on a hammerhead launch vehicle at transonic speeds are predicted by coupling CFD analysis and semi-empirical methods. From the RANS simulation, shock oscillation region, separation region, and separation reattachment region are identified, and the boundary layer thickness, the displacement thickness, and flow properties at boundary layer edge are calculated. The pressure fluctuations and power spectra on the hammerhead fairing are predicted by coupling RANS results and semi-empirical methods considering spatial distribution, and compared with the experimental data.

• Journal of the Korean Society of Systems Engineering
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• v.19 no.1
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• pp.56-63
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• 2023

For the success of system development, it is necessary to systematically manage the requirements that are the basis of system development and its verification results. In order to follow the principles of SE(Systems Engineering)-based V&V(Verification&Validation) process, requirements can be managed by securing the requirements and their establishments, design compliances, and verification compliances according to the system development lifecycle. Especially, in a large-complex system research and development project, such as a space launch vehicle development project, many participants establish, verify, and validate numerous requirements together during the project. Therefore, logical and systematic requirements management, including guarantee of data integrity, change history, and traceability, is very important for multiple participants to utilize numerous requirements together without errors. This paper introduces the practical requirements and verification management for the requirements-based development process in the space launch vehicle development project.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.8
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• pp.662-670
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• 2018

The altitude compensation nozzle is a nozzle designed for optimum performance at all altitudes. A method of improving the specific impulse of the space launch vehicle is a method of improving the characteristic exhaust velocity which is a characteristic of the combustion chamber and a method of improving the thrust coefficient which is a characteristic of the nozzle. The altitude compensation nozzle enables improvement of the performance of the space launch vehicle by improving the nozzle performance for the same combustor. Research on altitude compensation nozzles has been actively carried out in the DLR in Germany and is being carried out in advanced countries such as the US, Russia, UK, Australia and Japan. In this paper, the technology trends and patent trends of altitude compensation nozzles are investigated and summarized. Based on this, the technical trends of altitude compensation nozzles is grasped and utilized as basic data for the study on the performance improvement of a launch vehicle.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.203-208
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• 2005

Electronic components for space launch vehicles are exposed to a severe vibrational environment at launch and flight. The structural reliability of each component can be verified using mathematical approaches. In order to verify the structural reliability, an important parameter is the natural frequency of PCB(Printed Circuit Board) assembly mounted electronic components on and housing mounted PCB assembly in. In this paper, in order to find natural frequencies of PCB assemblies and the housing of hydrazine TCU(Thruster Control Unit), FEM(Finite Element Method) is adapted. The analytical result of FEM is verified by experimental method.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.133-140
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• 2004

In some cases, the launch vehicle is fatally affected by the change of weather condition. Thus the real time monitoring of weather condition is indispensible for successful launch campaign. This paper described general characteristics of weather radar for space center. The analysis of weather radar requirements has been carried out focusing on the transmitting power, gain of antenna, half power beam width, and minimum detectable signal.

• Proceedings of the KIEE Conference
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• 2006.10c
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• pp.407-409
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• 2006

우주발사체I 상단 시스템은 비행 중에 킥 모터 점화, 위성분리와 같은 HBW 점화기 기폭이 순차적으로 발생 한다. HBW 점화기의 기폭시에는 일반적으로 전도성 구조물을 통한 단락전류가 일시적으로 발생한다. 이러한 단락전류는 구동 전원 측으로 최대 전류 값 및 루프 면적에 비례한 일시적인 자기장을 형성시키고 near 필드(${\lambda}/2{\pi}$) 내의 인접하게 위치한 하니스에 자계 결합을 통한 역기전력 발생의 원인이 될 수 있다. 이러한 인접 하니스에 자계 노이즈 결합은 여러 자료를 통해 우주시스템 환경에서 일시적인 데이터 손실의 원인이 되는 것으로 분석되고 있다. 본 논문은 우주발사체의 HBW 점화기 기폭시 발생되는 전도성 구조물 단락전류 귀환현상으로 인한 자계노이즈 분석 및 감쇄방안에 대해 논의하고자 한다.

• 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 Society for Aeronautical & Space Sciences
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• v.39 no.8
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• pp.774-787
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• 2011

This paper deals with quantitative analysis about the characteristics of GNSS(Global Navigation Satellite System) signals contaminated with multipath signals and day-to-day repeatability of the navigation solution and SNR(Signal to Noise Ratio) caused by multipath signals using the collected data from GPS receiver installed on KSLV-I which was on standby on the launch pad at Naro Space Center. Since the GPS antennas, surrounding environments and GPS satellite orbits were very slightly changed with respect to the day, the repeating pattern of the solution and SNR caused by the multipath signals was verified from the collected data. Analytic result of the multipath effects and day-to-day repeatability of the navigation solution and SNR observed at the launch pad would be used for obtaining more stable performance of the GPS receiver when the satellite launch vehicles are on standby.

• Journal of Korean Society of Industrial and Systems Engineering
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• v.30 no.3
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• pp.165-173
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• 2007

A space launch vehicle system represents a typical example of large-scale multi-disciplinary systems, consisting of subsystems such as mechanical structure, electronics, control, telecommunication, propulsion, material engineering etc. A lot of cost is required to develop the launch vehicle system. A precise planning of R&D cost is very essential to make a success of the launch vehicle development program. Especially in the early development phase of a new space launch vehicle system, cost estimation techniques and analogy from past similar development data are very useful methods to estimate a development cost of the launch vehicle system. Now Korea Aerospace Research Institute is in charge of the KSLV-I (Korea Space Launch Vehicle-I) Program that is a part of Korea National Space program. KSLV-I Program is a national undertaking to develop launch capabilities to deliver science satellites of a 100kg-class into a low earth orbit. It is hereafter, going to plan to develop a new korean space launch vehicle. In this paper, first the development costs of well-known launch vehicles in the world are presented to provide a reference to make a development plan of a new launch vehicle. Second this paper introduces the present status of cost estimation applications at NASA. Finally this paper presents the results from application of a TRANSCOST, a parametric cost model, to derive a cost estimate of a new launch vehicle development, as an example.