• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.66-76
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• 2005

In this study, star visibility analysis of a star tracker is performed by using a statistical apprach. The probability of the Sun and the Earth proximity, the solar array masking probability, and the solar array blinding probability by the Sun light are obtained from the arbitrary chosen satellite positions as a function of a line of sight vector of the star tracker in several satellite attitude modes. This analysis demonstrates that the optimized star tracker accomodations can be determined to be an elevation angle -40o and two azimuth angles $-35^{circ}$ and $-150^{circ}$.

• Proceedings of the Korea Committee for Ocean Resources and Engineering Conference
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• 2004.05a
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• pp.48-53
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• 2004

In this paper, the task-oriented optimal configuration in the sense of Velocity and Force manipulability measure of manipulator mounted on ROV is considered. Manipulability is a quantitative measure of manipulator's capability obtained under the limits of joint velocities or torques. The base arrangements and optimal joint configuration of manipulator, that maximize the manipulability measure under the constraints of given task, are investigated. With the two types of base arrangements of manipulator, workspace analysis is carried out to investigate merits and demerits of each arrangement on the view of manipulability measure. To find optimal joint configuration for a given task with each arrangement, the SQP(Sequential Quadratic Programming) optimization are performed. Weighted linear combination of velocity and force manipulability measure is object function for SQP optimization. The kinematic parameters of Dual Orion manipulator which will be mounted on KORDI ROV are used for simulation.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.1
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• pp.42-49
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• 2014

Performance evaluation was carried out for the 70 N-class hydrazine thruster whose design performance had been already verified. The pulse-mode firing test was conducted for the development model thrusters with various thrust chamber diameters. Evaluation was made by the performance parameters such as specific impulse, impulse bit, and characteristic velocity, etc: specific impulse and characteristic velocity were deteriorated as the thrust chamber diameter deviates from a standard model. Consequently, it is revealed that the performance characteristics of standard model is most superior among the test models.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.83-92
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• 2004

This paper concerns servo filter design for KSR-III gimbal engine actuation system. When the actuator system is attached to engine mount frame, unexpected resonant modes in low frequency can occur and make the control system unstable. In order to prevent the resonance in the actuation system, a proper lowpass servo filter is designed. Based on the dynamic test data including the resonant effect, the shape of the servo filter is determined, and then the corresponding parameters are optimally designed. The best solution is finally selected via dynamic tests including the servo filter.

• Journal of Astronomy and Space Sciences
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• v.11 no.2
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• pp.308-319
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• 1994

We can launch satellites only at a certain time which satisfies special conditions, since the current techniques cannot overcome these constraints. Launch window constraints are the eclipse duration, solar aspect angle, attitude control, launch site and the launch vehicle constraints, etc. In this paper, launch window is calculated that satisfies all these constraints. In calculating launch window, the basic concepts are relative locations of the sun-satellite-earth system and relative velocities of these, and these requires geometric consideration for each satellite. Launch window calculation was applied to Kitsat 2(low earth orbit) and Koreasat(geostationary orbit). The result is shown in the form of a graph that has dates on the X-axis and the corresponding times of the given day on the Y-axis.

• The KIPS Transactions:PartD
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• v.12D no.2 s.98
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• pp.189-198
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• 2005

XML is rapidly becoming the standard for data representation and exchange, and XML documents are being adopted in various applications. Since the late 1990s, some native XML database management systems(DBMSs) have been developed. More recently, commercial relational DBMS vendors try to incorporate full functionalities of XML into their products, such as Oracle, MS SQL and IBM DB2. In this paper, we implement a well-known RDBMS-based XML data storage and indexing technique, called XPath Accelerator, and tune it in an industry-leading RDBMS. Our contributions are two-folds: 1) an in-depth implementation of the XPath Accelerator technique and 2) its tuning to exploit the advanced query processing techniques of an RDBMS.

• Proceedings of the KSRS Conference
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• 2008.03a
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• pp.207-212
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• 2008

연구에서는 SPOT-3 인공위성 영상으로부터 얻어진 영상 스테레오 스트립과 GCP(Ground Control Point)자료를 이용하여 다양한 GCP배치에 따른 궤도기반 센서모델의 정확성에 대해 분석하였다. 실험에 사용된 기준점자료는 춘천지역에서부터 나주지역에 이르기 까지 약 420km 길이의 지역에 대해 GPS측량을 통해 획득하였다. 궤도기반 센서모델에 적용된 미지수는 위성의 위치와 속도, 자세를 표현하는 방정식의 계수를 미지수로 선택하여 일곱 가지 방식으로 조합하였다. 실험은 우선 모델점의 위치를 일곱 가지 경우로 결정하고 각 경우에 대해 일정한 개수의 모델점을 선택하였다. 그리고 각 경우의 모델점의 위치에 대해 궤도기반 센서모델의 미지수 조합 모델을 각 각 다르게 적용해 본 후 그 결과를 시각적, 수치적으로 분석해 보았다. 실험 결과 모델점의 위치에 관계 없이 궤도기반 모델에 적용할 수 있는 높은 정확도를 나타내는 미지수 조합모델을 찾아낼 수가 있었고, 여러 가지 모델점의 위치를 궤도기반 센서모델에 적용해 본 결과 지리적, 시간적, 경제적 효율성을 갖는 최적의 미지수 조합을 찾을 수가 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.8
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• pp.641-651
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• 2020

This paper implements an antenna selection logic that automatically selects omni-directional antennas mounted on the top and bottom of an unmanned helicopter to maintain the link margin of the data link at 0dB or higher during flight. The selection criteria were derived by simulating and analyzing the radiation pattern. In addition, it is implemented to select the optimal antenna in real time during the flight by deriving the directivity angle function.

• The Bulletin of The Korean Astronomical Society
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• v.36 no.2
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• pp.110.1-110.1
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• 2011

오리온 A 분자운은 별탄생이 활발하게 일어나는 영역이다. 때문에 분자운 연구를 통해서 별탄생을 연구하기에는 최적의 곳이다. 특기할 것은 Orion A에는 필라멘트 구조가 있다는 점이다. 필라멘트는 전형적으로는 길이 4.8pc, 너비 1.4 pc 로 제시되었다(Nagahama et al. 1998). 많은 미지의 조건들 가운데 필라멘트 구조는 별탄생에 대한 새로운 조명을 던져주는 데, 가령 분자운이 수축, 분열하며 작은 덩어리를 만드는 과정에 이런 기다란 구조가 별탄생에 어떤 과정에서 나타나며 이것이 별탄생이 어떤 효과를 발생하는지 연구되어야 하는 문제들이다. 대덕전파안테나의 1분의 분해능(Channel resolution 63 KHz/ Band Width 25 MHz) 의 12CO, 13CO(J=1-0) 분자선 관측으로 필라멘트를 이전 연구보다 자세하게 관측하여 이것 안에 있을 것으로 보이는 substructure들 연구하고자 한다. 관측영역은 적경: 5h 32m ~ 5h 37m, 적위: $-5^{\circ}$ 14' ~ $-5^{\circ}$ 37'으로 ($1^{\circ}{\times}1^{\circ}$) 영역을 관측하였다. 그 결과 필라멘트구조를 확인할 수 있었으며 약 0.7pc,약 $1000\;M_{\odot}$의 덩어리들이 이전관측에서 보여진 X자형태가 아니라 일자형태로 분포되어있는 것을 알 수 있었다. 관측된 최소덩어리는 star cluster mass이고 stellar size 의 덩어리는 별탄생 과정 이후 소멸된 것으로 보인다. 관측으로 확인된 덩어리들의 물리적인 성질과 분포를 깊이 연구해 보고자 한다. 향후 Orion A 전체를 추가로 관측하고자 한다.

• Journal of Institute of Control, Robotics and Systems
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• v.17 no.10
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• pp.1006-1013
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• 2011

In this paper, we propose an optimal posture control law for an unmanned bicycle by deriving linear bicycle model from fully nonlinear differential equations. We calculate each equilibrium point of a bicycle under any given turning radius and angular speed of rear wheel. There is only one equilibrium point when a bicycle goes straight, while there are a lot of equilibrium points in case of turning. We present an optimal equilibrium point which makes the leaning input minimum when a bicycle is turning. As human riders give rolling torque by moving center of gravity of a body, many previous studies use a movable mass to move center of gravity like humans do. Instead we propose a propeller as a new leaning input which generates rolling torque. The propeller thrust input makes bicycle model simpler and removes input magnitude constraint unlike a movable mass. The proposed controller can hold optimal equilibrium points using both steering input and leaning input. The simulation results on linear control for circular motion are demonstrated to show the validity of the proposed approach.