• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.21-25
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• 2017

The umbilical system used for launch vehicle is to connect all ground supply lines (Pneumatic, hydraulic and electrical) to launch vehicle and disconnect those at few second before launch vehicle lift-off (or simultaneously with launch vehicle lift-off). During launch preparation stage, all umbilical shall be securely connected and also at separation stage, separation of all umbilical line shall be guaranteed. Therefore finding an appropriate connection force is a key factor on development of umbilical system. According to these design requirement, various kind of umbilical system has been developed from early stage of space development till today. In this paper, various kind of umbilical system developed so far is introduced according to its feature and operational concept. Also, umbilical system used for KSLV-II is introduced

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.8
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• pp.654-660
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• 2014

In this paper, a conceptual design of a launch vehicles is proposed by combining Naro-1 and KSLV-II. For trans-lunar injection (TLI) to lunar orbit at 300 km LEO, the target performance is defined same as that of KSLV-II, which delivers an object of 2.6 tons into 300 km LEO. The proposal launch vehicle concept of this study is combination of 1st stage of KSLV-I and 2-3rd stage of KSLV-II. Thus, it is possible to reduce the development time and also could expand the options for national launch vehicle capabilities with proven technologies.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.222-231
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• 2004

LCS(Launch Control System) in Space Center performs the ground and flight tests of launch vehicle. Those tests require data monitoring and control functions to the external systems such as launch vehicle, launch pad, and propellant supply system, etc. The LCS is composed of real time control system, simulation system, data server, external network, etc. The purpose of the simulation system is to simulate launch vehicle, and it is used for evaluation test of the LCS. This paper described the simulation system overview, the concept design, and the real time data processing evaluation tests of the simulator, gateway, data distribution server which are constituents of the simulation system.

• 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 of Propulsion Engineers
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• v.22 no.4
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• pp.1-11
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• 2018

A system design and integrated design process for a space launch vehicle were established based on system engineering. With the mission design results for a given payload weight and trajectory, it is possible to perform optimal design by integrating each unit such as propulsion, weight estimation, and aerodynamic force after analysis, during in the system design process. The program is finally configured to verify that the designed vehicle can perform its mission through 3-DOF trajectory optimization simulation. Genetic algorithms are used as the optimization method, and the optimal design results of the variables and parameters to be considered during design are presented.

• International Journal of Aeronautical and Space Sciences
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• v.15 no.4
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• pp.383-395
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• 2014

According to the requirement of wing weight estimation and frequent adjustments during aircraft conceptual design, a wing weight estimation method considering the constraints of structural strength and stiffness is proposed to help designers make wing weight estimations rapidly and accurately. This method implements weight predictions on the basis of structure weight optimization with stiffness constraints and strength constraints, which include achievement of wing shape parametric modeling, rapid structure layout, finite element (FE) model automated generation, load calculation, structure analysis, weight optimization, and weight computed based on modeling. A software tool is developed with this wing weight estimation method. This software can realize the whole process of wing weight estimation with the method and the workload of wing weight estimation is reduced because much of the work can be completed by the software. Finally, an example is given to illustrate that this weight estimation method is effective.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.898-903
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• 2011

Units assembled in the liquid-propellant propulsion system of launch vehicles should guarantee their on- and off-design performances under the various environments as well as at the various operation modes for the launch preparation and flight of launch vehicles. Units of liquid-propellant propulsion system can be installed in launch vehicle to insert satellite(s) into target orbit(s) only under the condition that all units must pass a series of tests to confirm whether those units perform normally as designed under the environment, which may be occurred in such stages of all development and operations as development, qualification, acceptance, assembly, pre-launch preparation, launch, and flight, and whether those units have been developed according to design requirements. Requirements for such tests have been already prepared in the advanced countries in launch vehicle systems based on experiences for decades. In Korea, where is now pursuing the development of KSLV-II, the research and development of launch vehicles using liquid-propellant propulsion system have been undergone during over 10 years. Hence test requirements for the development of units consisting of liquid-propellant propulsion system should be defined and Koreanized according to the domestic environment and circumstances and based on the experiences accumulated. In this paper requirements for the tests of units in liquid-propellant propulsion system, which can be feasible domestically, have been reviewed and defined.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.801-804
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• 2011

The concept design of joint part between propellant tank and feeding line for launch vehicle has been performed with the case study of oversea launch vehicles. we carried out, for the several configurations, numerical flow analyses to find the joint configuration which promises high flow uniformity at the outlet. There were a little difference in the numerical results, because the length of feeding lines are sufficiently long to stabilize the flow field.

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.239-242
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• 2004

The fairing of the launch vehicles has a role of protecting the spacecraft from outer thermal, acoustical, and mechanical loads during flight. Among them, the thermal load is analyzed in the present study. The ascent thermal analyses include aerodynamic heating rate on every point of the fairing, heat transfer through the fairing and spacecraft, and the final temperature during ascent flight phase. A design code based on theoretical/experimental database is applied to calculate the aerodynamic heating rate, and a thermal math program, SINDA/Fluint, is considered for conductive heat transfer of the fairing. The results show that the present design satisfies the allowing temperature of the structure. Another important thermal problem, pyro explosive fairing separation device, is calculated because the pyro system is very sensitive to the temperature. The results also satisfies the pyro thermal condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.167-170
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• 2008

A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.