• Journal of the Korean Society of Systems Engineering
• /
• v.10 no.2
• /
• pp.81-87
• /
• 2014

The Korea space launch vehicle-II (KSLV-II) program aims at developing a national launch vehicle system capable of launching 1.5 ton satellite into a sunsynchronous orbit. It is the succeeding program to the Naro launch vehicle program. The KSLV-II is a large-scale complex system which requires a systematic approach to all parts of the program. The KSLV-II program is currently developing a tailored systems engineering process for its need. It references practices and lessons learned from developing Naro launch vehicle. Standardized NASA processes and INCOSE processes were also referenced and compared during development of the process framework. This paper introduces the systems engineering processes developed for the KSLV-II program.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1122-1126
• /
• 2017

KSLV-II ullage motor is a type of the separation motor of Korea Space Launch Vehicle. Simultaneously operates with the retro Motor to perform the stage separation. The internal ballistics design, application of propellant composition, and the design of the combustion chamber and the canted nozzle were performed in accordance with the target performance of the ullage motor. Ti-6Al-4V alloy was applied to the combustion as material of chamber and nozzle. The heat resistant material of the nozzle was selected to ensure the heat resistance of the propellant containing a large amount of aluminum. And the combustion performance of the ullage motor satisfying the KSLV-II requirements was secured by performing the ground combustion test.

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

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

• 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 Aeronautical & Space Sciences
• /
• v.42 no.8
• /
• pp.654-660
• /
• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.598-602
• /
• 2017

Korea Aerospace Research Institute has been developing 3-stage launcher KSLV-II, which can inject 1.5-ton satellite into sun synchronous orbit (SSO). For development process, Test Launch Vehicle(TLV) adopting the $2^{nd}$ and $3^{rd}$ stage of KSLV-II will be scheduled to launch in 2018. The propulsion system of TLV is composed of $2^{nd}$ stage engine system (ground type) and propellant supply system including LOX, Kerosene tanks. Until now, system integration of engineering model of TLV and delivery of qualification model have been done. In this paper, the product assurance activities for propulsion system KSLV-II will be illustrated.

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

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.5
• /
• pp.107-114
• /
• 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 Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1171-1175
• /
• 2017

Cryogenic helium gas is used as the pressurant for the oxidizer pressurization of DR(Damper Receiver) sphere in the PSD(Pogo Suppression Device) system and liquid oxygen is used as the oxidizer for the propellant in Korea Space Launch Vehicle-II. The helium gas is stored in pressurant cylinders inside the cryogenic liquid oxygen tank and liquid oxygen is stored in the oxidizer tank. In this study, the performance test of PSD liquid oxygen drain valve for KSLV-II was considered.