• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1180-1183
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• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.479-483
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• 2012

This paper describes the development status of rocket engine test facility for the performance evaluation of liquid rocket engine of KSLV-II 1st stage. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the basic design of rocket engine test facility will be used as base data for the detail design and construction of rocket engine ground test facility of KSLV-II 75tonf liquid rocket engine.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1171-1175
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• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.30-35
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• 2017

The mechanical ground support equipment of KSLV-II launch complex is a collection of systems for transporting, erecting, lowering the launch vehicle and for providing an interface to supply propellants to the launch vehicle. In this paper, compositions, functions and design results of mechanical ground support equipment are introduced. In addition, the operation concept of each equipment along with operation procedure is presented.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.1
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• pp.50-57
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• 2021

Engine cool down process is necessary for the liquid rocket engines using cryogenic propellants in order to meet the requirement of engine inlet temperature. This paper evaluates the cool down characteristics of oxidizer supply pipeline and engine in prechill process prior to the engine firing tests, and calculate the quantity of liquid oxygen consumption.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.71-80
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• 2010

The KSLV-II(Korea Space Launch Vehicle-II) which being a successor of the KSLV-I is a space launch vehicle capable of delivering 1.5 ton-class satellite into a low earth orbit. The development of a 75 tonf-class liquid rocket engine(LRE) is planned on the basis of the technologies mastered through the preceded research of a 30 tonf-class LRE. The thrust chamber of the LRE is required to have higher combustion stability, structural integrity and thermal durability. This paper deals with the design requirements of the 75-tonf thrust chamber and a variety of technical considerations which have been conducted analytically in the course of the design for the realization of the requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.14-20
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• 2017

In this paper, KSLV-I flight test data and critical design results of filling operation for liquid oxygen filling system are compared to validate the reliability of the critical design modeling. Applying the filling and operation conditions on the critical design modeling, comparison of major flow rates and pressure values between test data and calculation results are conducted.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1200-1203
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• 2017

Propulsion system test complex (PSTC) is designed to verify propulsion system of KSLV-II. It is composed of hydraulic and pneumatic system, test stand system, control/measurement system, and flame deflector and safety system. In this study, kerosene filling system of hydraulic and pneumatic system is introduced. It performs store and chilling of kerosene, chilling and purging of filling line, and filling and retrieval of the kerosene. The kerosene supply requirements of 1, 2 and 3 stages of KSLV-II are considered in design process.