• Aerospace Engineering and Technology
• /
• v.12 no.1
• /
• pp.81-86
• /
• 2013

This article deals with the manufacturing and performance evaluation on the specimen pipes which have large size diameter and thin thickness. This specimen is for LOX main pipe of KSLV-II propulsion feeding system. The material of specimen is alloy 21-6-9. Alloy 21-6-9 has higher strength and better weldability rather than STS-300 class pipes. We found that the specimen using alloy 21-6-9 satisfied the requirement by pressurization tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1169-1170
• /
• 2017

Engine System Development Document management system(ESDD) 2.0 has already been operated for systematic engine systems development of KSLV-II. In addition, ESDD 3.0 is under development to manage the documents of before and after engine tests. In this paper, the concept and direction of ESDD 3.0 will be briefly described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1184-1187
• /
• 2017

The space launch vehicle needs the verification of each stage's propulsion system. The Propulsion System Test Complex(PSTC) is constructed for developing KSLV-II in the Naro space center. Hydraulic and pneumatic system of PSTC should supply propellants and various gases to propulsion system module according to required condition. This paper introduces liquid oxygen filling system of PSTC.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.479-483
• /
• 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
• /
• 2012.05a
• /
• pp.507-514
• /
• 2012

In the present research, NASA LRB plume radiation models are reconstructed with Thermal Desktop software, where the radiation to vehicle base environment can be calculated. The calculation shows the similar radiation heat compared to NASA prediction. Based on LRB plume radiation model, a KSLV-II thermal radiation model is proposed.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.1
• /
• pp.68-76
• /
• 2022

Upper stage of the Korea Space Launch Vehicle-II(KSLV-II) uses a 7-tons class liquid rocket engine and is an open gas generator cycle with a turbopump supply method that uses kerosene/liquid oxygen as the propellant combination. This study first provided a brief overview of the design and development process of the upper stage engine. In addition, it introduced the solutions and results applied to some of the problems that occurred during the development process of the upper stage engine.

• Journal of Aerospace System Engineering
• /
• v.11 no.3
• /
• pp.22-30
• /
• 2017

This paper examines a survey on recent research regarding health monitoring and management for liquid rocket engines (LRE). For this, we investigated precedent techniques applied to LRE development. Particularly, we focused on open-cycle LRE to apply to KSLV-II (Korea Space Launch Vehicle II). Through this study, we subdivided health monitoring algorithms and analyzed fault detection and diagnosis algorithm developed in China, since China researched open-cycle LRE that have the same cycle as KSLV-II rocket engines. We discuss significant points to be considered regarding development of the KSLV-II.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.5-13
• /
• 2017

To lunch the Korea Space Launch Vehicle-II(KSLV-II), the second launch complex will be constructed on the Naro Space Center and Kerosene Filling System (KFS) will be also installed newly. KFS of KSLV-II launch complex system is being designed based on Naro Launch Complex. But this must supply fuel to fuel tanks of the vehicle with only a supply pump because KSLV-II is a 3-stage launch vehicle unlike Naro Launch Vehicle or Test Launch Vehicle (TLV). A sudden rise of pump output pressure is recognized during fuel filling scenario selection process. This occurs because return flow can not actively deal with a lot of flow change using flow control method of orifice type. To solve this problem, it is verified that fuel can be stably supplied by installation of accumulator and an appropriate adjustment of filling mode change sequence through flow analysis of various cases.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.5
• /
• pp.132-140
• /
• 2018

To lunch the Korea Space Launch Vehicle-II(KSLV-II), a second launch complex will be built at the Naro Space Center, and a Kerosene Filling System (KFS) will be installed. KFS of KSLV-II launch complex system is being designed based on Naro Launch Complex. But this must supply fuel to fuel tanks of the vehicle with only a supply pump because KSLV-II is a 3-stage launch vehicle unlike Naro Launch Vehicle or Test Launch Vehicle (TLV). A sudden rise of pump output pressure is recognized during fuel filling scenario selection process. This occurs because return flow can not actively deal with much flow change using the orifice-type flow-control method. To solve this problem, it is verified that fuel can be stably supplied by installing an accumulator, designed for appropriate adjustment of filling-mode change sequence via flow analysis of various cases.