• Proceedings of the KIEE Conference
• /
• 2000.11d
• /
• pp.721-723
• /
• 2000

국내 과학관측 로켓(Korea Sounding Rocket-III; 이하 KSR-III) 발사통제 시스템 개발 중 로켓 임무 달성에 필요한 시스템 구성과 제작에 대한 전반적인 설계내용을 기술하였다. 로켓 임무와 설계 요구 조건에 의해 각 통제 콘솔과 발사 상황판은 설계되었고 현재 제작 중에 있으며. 향후 KSR-III 발사시험 시 활용 할 계획이다.

• 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
• /
• 2008.11a
• /
• pp.72-77
• /
• 2008

The function of the Reaction Control System include roll, pitch and yaw control of the launch vehicles and fine control maneuvers and precision upper stage orientation before separation of one or more payload. This paper describes the overview of commercial launchers, current technology trend for RCS of launch vehicles, and development status of medium class thruster for RCS.

• Aerospace Engineering and Technology
• /
• v.2 no.2
• /
• pp.167-178
• /
• 2003

The design on the Telemetry Ground System for launch of KSLV(Korea Space Launch Vehicle) in the korean Space center has been conducted in this study. For the optimized system design, first of all, the system deployment plan reflecting the topographic and geographic environments of the space center and launch vehicle characteristics has been developed. The RF link budget analysis for the maximum tracking range, requirement for receiving subsystem including antenna subsystem, requirement for data processing subsystem are also analyzed based on the On-Board Telemetry characteristics and launch vehicle parameters. Based on those analysis, telemetry ground system containing tracking/receiving subsystem, recording subsystem and data processing subsystem, timing subsystem, calibration subsystem and monitoring and control subsystem are designed. Futhermore, the analysis for the maximum permissible data latency and communication protocol between each telemetry station and control center are conducted and the entire system is designed so that the major telemetry parameters selected to the best quality are provided in real time to the control center(RCC, RSC) for the launch mission operation.

• Journal of Astronomy and Space Sciences
• /
• v.15 no.2
• /
• pp.373-389
• /
• 1998

The test result of the X-ray observation system is presented which have been developed at Korea Astronomy Observatory for 3 years(1995 -1997). The instrument, which is composed of detector and signal processing parts, is designed for the future observations of compact X-ray sources. The performance of the instrument was tested by mounting on the two-stage Korean Sounding Rocket, which was launched from Taean rocket flight center on June 11 at 10:00 KST 1998. Telemetry data was received from individual parts of the instrument for 32 and 55.7 sec, respectively, since the launch of the rocket. In this paper, the result of the data analysis based on the received telemetry data and discussion about the performance of the instrument is reported.

• Aerospace Engineering and Technology
• /
• v.10 no.1
• /
• pp.116-121
• /
• 2011

The tracking radar systems in NARO space center are used in order to acquire the TSPI (Time, Space, and Position Information) data of the launch vehicle. The tracking radar produce the measurements of tracked targets in the radar-centered coordinate system. When the tracking radar is in the Cartesian/Polar tracking mode, the state vector data is sent in radar-centered Cartesian/Polar coordinate system to RCC. RCC also send the slaving data in Test Range coordinate system to the tracking radar. So, the tracking radars have to transform the slaving data in Test Range coordinate system into in radar-centered coordinate system. In this study, we described the coordinate transformation between radar-centered coordinate system and Test Range coordinated system.

• Aerospace Engineering and Technology
• /
• v.11 no.2
• /
• pp.103-108
• /
• 2012

There is close correlation between the reliability of the launch vehicle and the leakage of the propellants or gases from the launch vehicle. This paper describes the definition of the leak rate to determine the quantity of the leakage and introduce the unit conversion of the leak rate. The main parameters for the leak rate were considered. The requirements for the gaseous for the leak test of launch vehicle and various leak test methods were introduced. Leak test method and procedure used in space launch vehicle were briefly described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1006-1010
• /
• 2017

This paper describes the design and test of the thermal control and fire safety system for thermal control and the fire/explosion prevention of inside the compartment during the preparation and operation of the space launch vehicle at the launch pad. The system considered here is for the test launch vehicle which is being developed as part of the development of the Korean Space launch vehicle-II. This system applies the high pressure system based on the heritage of Naro launch vehicle. The selection of thermal control and fire safety system from high pressure and low pressure system is done in consideration of the characteristics of the launch pad gas supply system and the characteristics of launch vehicle, and the system configuration is also changed accordingly. As a result, it has been confirmed that the developed system satisfies the initial design conditions through the test. Moreover the system will be applied to the development of the Korean launch vehicle in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.293-298
• /
• 2005

Air-Launching is an effective method that can launch the 'Nanosat' with low launching cost. In this study, system and subsystem design of the air launching rocket for nanosats which perform a simple mission, have been performed. Foe this purpose, the WBS of the Air-launching Rocket System, and the subsystem schematics have been defined first. Based on these results, detailed configuration and DMU have been developed.

• Aerospace Engineering and Technology
• /
• v.2 no.1
• /
• pp.140-152
• /
• 2003

Scenario is a guiding principle of launch operation and control for rocket and ground support system. Therefore, developing a scenario is the first step to prepare for rocket launch, which is a critical task for success of KSR-III flight test. The launch scenario for KSR-III flight test is a procedural sequence of command and control signals to be given to rocket and ground support systems. In this paper, the UML object modeling method is applied to development of a launch scenario. First, the subsystems of the launch system are modeled by objects, and then the interfaces between each two subsystems are modeled by association links. The finally obtained object diagram of KSR-III launch system is used to analyzing flow of data and commands and control signals, and interactions. The scenario includes the sequences of pre-launch/launch operations and emergency operations.