• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.6
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• pp.533-538
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• 2007

A semi-passive vibration isolation control method for enhancing pointing performance of on-board payload has been derived, and its effectiveness has been evaluated through numerical simulation. The semi-passive control law proposed in this study was derived so as to obtain the same performance as a high passive damping at low frequencies and obtain the same performance as a passive low damping at high frequencies. In the numerical simulation, the intended vibration isolation performance of the semi-passive control law has been obtained.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.108-108
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• 2003

본 논문에서는 과학위성 2호의 주 탑재체인 LIST의 Operation에 대한 개념을 소개하고자 한다. LIST는 태양 진공자외선(Lyman-$\alpha$)의 full disk 영상을 획득하고 분석함으로서 채층과 전이영역의 구조와 진화, ‘Quiet Sun’의 진공자외선 복사 변화 모델, 그리고 태양 진공자외선의 복사로 인한 지구 고층 대기의 변화를 밝혀내는 것이 목표이다. 이러한 목표를 성공적으로 수행하기 위해서는 LIST Operation 개념의 정립과 철저한 규정이 필요하다. 따라서 본 연구진은 Operation을 크게 두 부분으로 세분하였다. 즉, LIST의 각 구성 요소들이 유기적으로 작용, 목적하는 데이터의 성공적인 획득을 위한 ‘Technical Operation’과 획득된 데이터를 활용하여 효과적으로 분석하고 목적한 과학적 성과를 달성하기 위한 ‘Scientific Operation’으로 구분하여 규정하였다. 또한 효율적인 Data System의 관리를 위해 데이터의 흐름을 ‘LIST Observing System’, ‘LIST Data Acquisition System’, ‘LIST Data Reduction and Analysis’, 그리고 ‘LIST Data Analysis and Publication’의 네 가지 단계로 나누어 Data의 활용 중에 나타날 수 있는 위험들을 최소화 하고자 하였다.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.11a
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• pp.161-164
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• 2005

This paper finds the optimal staking sequence of the satellite composite structures to minimize severe thermal deformations during their orbital operation using GAs and finite element analyses. Then, the optimal design is reinforced to endure the launch loads like high inertia and vibratory loads that are, usually, smaller than orbital loads induced by space environments. The thermal deformation of sandwich panels was minimized at the staking sequence of [$0_2$/90]s and that of composite strut was lowest at the angle of [0/${\pm}45$]s Also there was no buckling in the compressive loading. By vibration analysis, the natural frequencies of the composite components are much higher than aluminum structures and the expected stiffness condition is satisfied. Then, a composite optical bench was fabricated for tests and all analyses results were verified by structural testing. There were good correlations between two results.

• Journal of the Korean Society for Precision Engineering
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• v.30 no.11
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• pp.1203-1210
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• 2013

Korea's first Naro-Science small class satellite was launched by Naro launcher in 2013. The structure of the satellite is mostly composed of aluminum honeycomb and frame. The honeycomb structure is homogenized with asymptotic homogenization method and its mechanical properties were used for the numerical analysis. There have been some difficulties to modeling the honeycomb sandwich panels for FEA. In the present study, the mechanical characteristics of the sandwich panel composite were numerically computed and used for the simulation. This methodology makes it easy to overcome the weakness of modeling of complicated sandwich panels. Both an experiment of vibration test and numerical analyses were conducted simultaneously. The analysis results from the current homogenization were compared with that of experiment. It shows a good agreement on the dynamic responses and certified the reliability of the present methodology when manipulate sandwich panel structure.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.60-65
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• 2007

Acoustic chamber was developed for verifying the performance of a satellite under the launch condition on the Space environment test department. As the size of a satellite is increased the extension of existing facility is required. This paper encompasses the following items; redesign of components in acoustic chamber, product procedures of them and review of the test for the components of satellite in the upgraded acoustic chamber.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2013.04a
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• pp.533-539
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• 2013

Number of components and payload systems installed in satellites were found to be exposed to various disturbance sources such as the reaction wheel assembly, the control moment gyro, coolers, and others. A micro-level of vibration can introduce jitter problems into an optical payload system and cause significant degradation of the image quality. Moreover, the prediction of on-orbit vibration effects on the performance of optical payloads during the development process is always important. However, analyzing interactions between subsystems and predicting the vibration level of the payloads is extremely difficult. Therefore, this paper describes the analytical and experimental approach to microvibration effects on satellite optical payload performance with integrated jitter analysis framework, micro vibration emulator and satellite structure testbed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.1
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• pp.56-62
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• 2011

A Satellite transponder is mounted on the Satellite and performs radio communications with the ground station. A Digital transponder compared to The analog transponder is made easy and accurate performance prediction. Also Modulation Scheme, Data Rate, Loop Bandwidth, Modulation Index and etc. can be changed on orbit, by implementing FPGA can reduce the weight and volume. The core technology of digital transponder is Carrier Recovery loop. Dynamic Range, Frequency Tracking Range, Frequency Tracking Rate and Coherent performance are determined by the performance of the Carrier Recovery loop. In this paper, we proposed the structure of Carrier Recovery loop for the Satellite digital transponder, then tested and verified the structure.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.114-119
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• 2007

This paper introduces modal test of the 2nd stage structure of KSLV-I which is composed to satellite, PLA(Payload Adapter), EB(Equipment Bay), KMS(Kick Motor Support) and KM(Kick Motor) without PLF(Payload Fairing). In this test, to simulate free-free boundary condition, test object was hung by 4 bungee cords and excited by using impact hammer. From this test, dynamic properties of the 2nd stage structure of KSLV-I can be obtained. Modal test data are analyzed by using TDAS(Test Data Analysis Software). As the result, modal parameters and mode shapes below 100Hz of the 2nd stage of KSLV-I were identified.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.25 no.1
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• pp.32-38
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• 2014

In this paper, we design a secant pattern antenna combined with a septum circular polarizer to be used in the satellite data communications. To generate a radiation pattern with secant type, Fourier relationship between current distribution and space factor is applied and the circular symmetric structure of the aperture simplifies the design. The optimization process is performed by combining the radiator with the septum circular polarizer, and it is confirmed that the designed radiation pattern, axial ratio, and return loss characteristics satisfies the required performance of the antenna.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.10 no.4
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• pp.582-593
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• 1999

This paper presents the design and fabrication of the diplexer for a KOREASAT-III Ka-band satellite transponder. The transmission characteristics of the diplexer is analyzed by calculating the generalized scattering matrix using mode matching method. It is composed of 2 bandpass filters, coupled with H-plane T-junction having symmetrical inductive iris and E-plane metal insert structures. Compared with the size and weight of the Rx and Tx filter loaded with a transponders respectively, those of the diplexer can be effectively reduced. In a high power transmission, the variation of the filter characteristics is minimized by the scheme that irises are extended to the exterior of H-plane of the waveguide. This scheme needs no extra heat sinks for dissipating high power. The diplexer is designed to improve the simplification, durability and reliability by eliminating tuning screws, which have been used to compensate for the characteristics of fabricated filters. The bandpass filters of the diplexer show the insertion loss of less than 1.2 dB and the return loss in excess of 15 dB. The isolations of more than 65 dB have been achieved between Rx and Tx filter.