• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.613-615
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• 2009

This paper is to introduce Hanwha Aerospace R&D Center's development status of TVC(Thrust Vector Control) system and control valves for Korean space launch vehicles. With the successful development of KSR-III TVC system, Hanwha have developed TVC system and RCS control valves for KSLV-I. Also, in the advance research area of KSLV-II, Hanwha have participated in LOx and fuel flow control valves and LOx shut-off valve development in the engine supply system. Based on the accumulated experiences and technologies in the aerospace key components and system development, Hanwha will make an important contribution to KSLV-II development in the future.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.171-179
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• 2007

The Test Equipment for the upper stage of KSLV-I has following functions via umbilical cable interface; external power supply, command output such as discrete and analog, data acquisition, CS-I interface simulation for first stage of KSLV-I and RS-422 serial communication for PDU. The main purpose of UTE is the experiment or function verification of system-level upper stage. To realize this system, we used PXI control system. The UTE is consisted of the PXI control system, power supply, terminal block, internal harness, connector panel and so on. The software functions of UTE are classified by four blocks. These are Discrete/Analog I/O control, PDU RS-422 serial communication control, power supply GPIB control and UTE remote control. In this paper, we will describe the design on the hardware and software of UTE.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.11
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• pp.1077-1085
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• 2011

Various stakeholder's expectations and constraints are to be efficiently resolved into a program consensus prior to the beginning of its substantial design processes. This study focuses on the analysis of the stakeholder's expectations in determining the design requirements at the initial stage of space exploration programs including Naro launcher and currently on-going KSLV-II program. Naro program seems to unilaterally account for the government expectations of accelerating program phase speed without making any efforts to converge various expectations from related sectors. The planning of Naro launcher is also found lack of the concept of operations (ConOps), which is of critical importance by envisaging the operational applications of end products. Similarities are found in KSLV-II program regarding the lack of implementation for stakeholder's expectations. Moreover, the government plan for KSLV-II disclosed without considering all expectations and other comments. The increase in design conflicts and program uncertainties would be unavoidable, if the government plan for KSLV-II would be insisted. It is required to modify the government plan and to establish the ConOps with the convergence of stakeholder's expectations at this early stage of the program.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.229-235
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• 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 the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.107-114
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• 2018

Korea Space Launch Vehicle (KSLV)-I flight test data and the modified 1-dimensional steady state modeling data from the critical design results of the KSLV-II liquid oxygen filling system operation are compared to validate the reliability of critical design modeling. A comparison of major flow rates and pressure values between test data and calculation results are conducted. The relative errors relative to maximum total flow rate for each cooling, filling, and replenishment mode are determined within 6.7%. Calculated pressure values at the outlet of the pump and the inlet of flow control valves are within 5.1%. The pressure at the inlet of the launch vehicle for each operation mode are within the measured pressure range.

• Proceedings of the Korean Society of Computer Information Conference
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• 2016.07a
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• pp.29-32
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• 2016

본 논문에서는 나로호(KSLV-I) 비행상태의 실시간 감시를 목적으로 국내에서는 처음 개발된 우주센터 원격수신자료전시시스템(EDS)의 구축과 운용을 소개한다. EDS는 우주센터 발사통제시스템의 주요 시스템 중 하나이고 그 역할은 위성발사체의 비행에 중대한 영향을 주는 주요정보(QLM)와 궤적정보(TSPI)를 수신하여 실시간으로 처리함으로써 탑재 서브시스템별 전문가들이 위성발사체의 비행 상태를 감시할 수 있도록 지원하는 것이다. EDS는 3회에 걸친 나로호 비행시험에서 그 역할에 따라 매회 8대가 운영되었으며 임무를 성공적으로 수행하였다. 본 시스템을 기반으로 추후 발전된 형태의 한국형발사체(KSLV-II) 비행상태의 실시간 감시시스템의 구축이 가능할 것으로 예상된다.

• International Journal of Aeronautical and Space Sciences
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• v.11 no.3
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• pp.184-192
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• 2010

In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.108-116
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• 2009

This paper considers the trajectory design problem for a lunar orbiter when launched by KSLV-II. KSLV-II puts its kick motor stage and lunar orbiter into a low earth orbit, and then the kick motor stage performed the translunar injection. To simulate more realistic situations, TLI (Trans-Lunar Injection) and LOI (Lunar Orbit Injection) maneuvers are modeled as finite burns. The feasibility of the lunar mission by KSLV-II are confirmed by the numerical results that show the reasonable required-velocity and propellant usage.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.119-125
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• 2007

Space launch vehicle development needs many kinds of technologies synthetically. Nowadays, KARI (Korea Aerospace Research Institute) has developed a space launch vehicle, KSLV-I (Korea Space Launch Vehicle-I), that is able to load with an 100kg payload. After that it plans to develop Korean Space Launch Vehicle. As space launch vehicle becomes more complicate and larger, it needs a scientific and analytic development cost estimation. In this paper a cost estimation for KSLV-II using TRANSCOST 7.1 was studied.

• Journal of Aerospace System Engineering
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• v.8 no.2
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• pp.49-54
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• 2014

The main purpose of Korea Space Launch Vehicle II(KSLV-II) Program is to develop a domestic launch vehicle that can deliver a 1.5ton class application satellite into a Low Earth Orbit(600~800km). The data management is an essential factor in systems engineering for success of large-scale complex systems development, and it systematically manages the information and technical data for the total life-cycle of a system. In this paper, data management policies and processes on KSLV-II program are presented, and product life-cycle management system for KSLV-II program is also presented.