• Journal of Advanced Navigation Technology
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• v.12 no.4
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• pp.295-303
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• 2008

Malfunction of satellite launch vehicles with high speed and long range can be a major concern for operations. Flight safety system that monitor the trajectory and identify any failure of the launch vehicles. Tracking filters for the flight safety systems are different from common tracking filters since filter reliability is more emphasized than accuracy. Reliable estimation of instantaneous impact points requires reliable velocity estimates as well as reliable position estimates. A fusion filter for a flight safety system was developed with the tracking sensor models for the Korea Satellite Launch Vehicle I. The fusion filter performances were evaluated by analyzing the trajectory and instantaneous impact point estimates.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2001.05a
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• pp.228-233
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• 2001

Satellite system experiences severe mechanical loads during the launch period. Therefore, positive margin of safety of the satellite system must be demonstrated for every possible mechanical loading condition during the launch period. This paper presents modal and stress analysis result due to quasi-static loads for the satellite antenna system. The failure tendency for the sandwich construction of the satellite antenna system has been studied with various lamination angles of unidirectional prepreg.

• 한국전산유체공학회:학술대회논문집
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• 2005.10a
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• pp.87-91
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• 2005

A conceptual design for the movable roll vane system is done for the roll stability control of KSLV-I. The control effectiveness of the roll vanes is estimated using the numerical simulation. The hinge location is selected to minimize the torque requirement at the maximum dynamic pressure condition, and the maximum torque of 3.0 kN-m is found to be required to actuate the roll vanes for the entire range of operation. An electro-mechanical actuator system which is composed of a DC motor, the speed reducers, the battery package and the controller is designed using the given requirements, the maximum torque of 3.0 kN-m, the maximum deflection angle of 25 deg. and the maximum angular velocity of 30 deg/sec. More detailed design to make more compact and highly efficient system will be done in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.491-494
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• 2005

This paper describes the fundamental research of hybrid-propellant rocket system focusing the flight. The performance of the hybrid-propellant rocket system (using the background of lab-scale tests) for a small-scale launch vehicle could have been validated by static thrust tests and flight tests. Based on this system, it was found that hybrid rocket propulsion system was available in an application to a launch vehicle system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.113-115
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• 2006

Consulting Stout & Snell's paper[1], design approaches for the pressurization system for a launch vehicle are introduced. We have outlined the typical system requirements and a dynamic model of the pressurization system. A brief summary on the control loop design for multiple on-off valve control systems has been also presented.

• Proceedings of the IEEK Conference
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• 2002.06e
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• pp.173-176
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• 2002

DAS(Data Acquisition System) as a ground support equipment has played a critical role in proving the status of ready-to-fire of a rocket system before launch. But it is hard to implement and place a real-time measuring system in a control room at a long distance from the vehicle. In this paper DAS is introduced by being located at the LEC(Launch Equipment Container)[1], 50 meters away from the rocket and connected to remote monitoring system via fiber optics with TCP/IP protocol by means of client/server algorithm. Therefore real-time data acquisition and storage are guaranteed and a convenient and useful MMI (Man-Machine Interface) can be developed.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.814-815
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• 2010

Korea Aerospace Research Institute plan to develop propulsion system test facilities for combustor, engine system, propulsion systems of KSLV-II propulsion system in process of Korea Space Launch Vehicle project. By review for heavy test facilities specifications of foreign technically developed nations of the world, it will be referenced for test facility development plan of Korea Space Launch Vehicle project in the future.

• Journal of Navigation and Port Research
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• v.38 no.4
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• pp.429-435
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• 2014

In general, Introducing of the Designated Manager System (DMS) of public facilities has been promoted as part of administrative reforms for planning improvement of service for customers by a private and budget cuts of operations management. DMS has begun to be introduced to the public marina facilities in earnest in 2006, it is evaluated positive about efficiency in terms of business(budget cuts). However, there is no discussion about efficiency (likes service satisfaction of client-side) from the marina whose major job is service. The primary purpose of this study is to clarify the benefits and challenges as a result of the Designated Manager System (DMS) launch implemented by local governments, following the relevant amendments to the Local Government Law. The second purpose is to clarify, from the viewpoint of users, what changes have taken place after the DMS launch, focusing on public marinas operated under the DMS. As for the primary purpose, the study is intended to clarify the economic benefits of the DMS and the significance of the DMS launch at a prefectural government level. This will help us assess whether it would be worthwhile to encourage private companies or non-profit organizations (NPO) to participate in the management and operation of public facilities under the DMS scheme. Most of the studies to date have examined the benefits of the DMS launch, focusing on the economic benefits for local governments. This study is intended to clarify the benefits and disadvantages to users of the DMS launch from the viewpoint of users.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.12
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• pp.950-958
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• 2013

The Lunar orbiter is expected to be inserted into a ~300km low Earth orbit using Korea Space Launch Vehicle-II(KSLV-II). After the states are successfully determined with obtained tracking data, the Trans Lunar Injection(TLI) burn has to be done at appropriate epoch to send the lunar orbiter to the Moon. In this study, we describe in detail the mission scenario of the Korean lunar orbiter from the launch at NARO Space Center to lunar orbit insertion(LOI) stage following direct transfer trajectory. We investigate the launch window including launch azimuth, delta-V profile according to TLI and LOI burn positions. We also depict the visibility conditions of ground stations and solar eclipse duration to understand the characteristics of the direct transfer trajectory. This paper can be also helpful not only for overall understanding of ${\Delta}V$ trend by changing TOF and coasting time but for selecting launch epoch and control parameters to decrease fuel consumption.