• Current Industrial and Technological Trends in Aerospace
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• v.4 no.1
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• pp.83-91
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• 2006

추적레이다는 표적으로부터 반사되어 돌아오는 신호 또는 질의 신호에 대한 응답 신호를 수신하여 표적을 추적하는 장비이다. 추적레이다가 표적을 추적하는 범위는 일반적으로 좁게 한정되므로 이동하는 표적을 추적하기 위해서는 먼저 안테나 빔의 지향각과 거리를 표적에 맞추고, 표적이 획득된 후에는 안테나 빔을 연속적으로 이동하는 표적을 향해 방사하여 표적을 추적하게 된다. 일반적으로 추적레이다가 표적을 추적하는 경우에는 과정 잡음과 측정 잡음에 의해서 발생되는 부정확성과 관심없는 표적이나 클러터 등으로부터 생성된 측정 근원의 부정확성으로 인한 문제가 발생하게 된다. 이러한 표적 추적에 따른 문제를 해결하기 위해서 많은 추적 알고리듬들이 개발되어 왔다. 이 논문에서는 가장 기본적인 표준 칼만 필터와 측정 근원의 부정확성에 따른 데이터 연관 문제를 고려한 여러 추적 알고리듬에 대해서 기술하였다. 또한 한국항공우주연구원 우주센터의 우주발사체 추적용 추적레이다에 대한 간략한 설명과 우주발사체 추적에 사용되는 추적 알고리듬에 대해서 소개하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.8
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• pp.681-688
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• 2021

This paper considers the trajectory and impact point dispersion analysis of the test launch vehicle (TLV). The analysis, which performed before and after its flight test on November 28, 2018, is described and verified by comparing with the flight test results. The six degree-offreedom (DOF) simulation is used to compute the dispersion of the trajectory, attitude, and impact point, where the launch vehicle performance variations and wind effects during the atmospheric phase are included. The impact area to guarantee the flight safety is determined using the results of the dispersion analysis. The flight test results confirm that the safe flight of TLV is performed within the predicted dispersion boundary.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.551-554
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• 2012

KARI is now developing KSLV-II which can insert 1.5ton satellite into the orbit, and system design review is close at hand. As a part of mission assurance for space launch vehicle, reliability and safety management is being performed and to assure the safety, KARI has been doing actions on the basis of the safety assurance plan and system safety program plan. In this study, preliminary hazard analysis is reviewed and the result for the propulsion system will be illustrated. The result will be used as a reference for the safety and risk management.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.20-29
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• 2011

There are a lot of electrical and electronic components and pneumatic parts sensitive to vibration and shock in the VEB assembly which KARI directly transports among the KSLV-I upper stage transportation items. So, the special attention in the transportation is required. The transportation container with the apparatus for controlling environment was made in order to meet the requirements. The transportation tests using the engineering model were performed 4 times to verify the performance of the transportation container and to conform the transportation conditions(transportation velocity, route, etc.). In this document, the previous transportation history of the VEB assembly, the overview and the result of the KSLV-I FM unit 2 VEB assembly transportation are described.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.280-287
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• 2010

The first Korean satellite launch vehicle, KSLV-I(Korea Space Launch Vehicle-I), was launched for its first flight test on Aug. 25, 2009 from Naro Space Center located in south Jolla province. Because launch vehicles usually fly long range with large amount of propellants aboard, preparation of countermeasures against potential malfunctions during flight is essential in launch operation. In this paper, the flight safety operation, prepared to guarantee flight safety during launch operation of KSLV-I, is presented. Prior to flight test, flight safety analysis is performed to estimate associated risk levels quantitatively, and during flight, flight safety systems are operated to cope with any risky situations. Real-time flight monitoring including computation of instantaneous impact point using tracking data is executed normally and the flight test is completed without activation of flight termination system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.17-26
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• 2005

Numerical investigation has been made on the aerodynamic characteristics of supersonic air-launching rocket, as a new concept launching mechanism. Parametric study on the variations of launching velocity, incident angle and mounting location of the rocket has been performed using three dimensional Euler equations. Influential factors at separating stage of the rocket were extracted through comprehensive analyses, and, the response surface models were constructed for those factors. From the study, the aerodynamic behavior of the air-launching rocket at supersonic speed and useful guidelines for the optimal mounting location of the rocket have been obtained.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.151-156
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• 2003

Liquid rocket engine system is classified into an engine of pressurization and turbo pump type by the way of fuel fed-supporting system. In the KSR-III sounding rocket, an engine of pressurization type was used, but there was lots of technical problems to be solved for a use as the first stage engine of space launch vehicle. So, an engine of turbo pump type was required to be developed to overcome the technical limitation of liquid rocket engine. In this research, the analysis of propellant of Kerosine-LOX and methane-LOX which are noticed as a future propellant was carried out for the purpose of studying the basic characteristics. And to review the basic characteristics of an engine of turbo pump type, among the sizing variant of the space launch vehicle, the ways of injecting a satellite to a direct orbit and transient orbit were discussed in this paper.

• Current Industrial and Technological Trends in Aerospace
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• v.3 no.1
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• pp.92-98
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• 2005

• Current Industrial and Technological Trends in Aerospace
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• v.2 no.2
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• pp.95-101
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• 2004

• Current Industrial and Technological Trends in Aerospace
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• v.1 no.1
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• pp.89-99
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• 2003