• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.6
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• pp.74-86
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• 2021

The composite lattice structure is a structure that supports the required load with the minimum weight and thickness. Composite lattice structure is manufactured by the filament winding process using impregnating high-strength carbon fiber with an epoxy resin. Filament winding process can laminate and manufacture only structurally necessary parts, composite lattice structure can be applied to aircraft fuselages, satellite and launch vehicles, and guided weapons to maximize weight reduction. In this paper, the development and evaluation of the composite lattice structure corresponding to the entire process from design, analysis, fabrication, and evaluation of large-scale cylindrical and conical composites lattice structure were performed. To be applicable to actual projectiles and guided weapons, we developed a cylindrical lattice structure with a diameter of 2,600 mm and a length of 2,000 mm, and a conical lattice structure with an upper diameter of 1,300 mm, a lower diameter of 2,500 mm, and a length of 900 mm. The performance of the developed composite lattice structure was evaluated through a load test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.586-594
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• 2009

This paper is the study on random, sinusoidal and shock vibration responses for the STSAT-3(science and technology satellite-3) proto-model which is the first small size all-composite satellite in Korea. The structure system of the STSAT-3 forms box type structure by joining several hybrid sandwich panels comprised of honeycomb core and carbon fiber reinforced laminated composite skins on both side. Mode shape, stress, displacement and acceleration responses are obtained on both the frequency domain and time domain by means of a commercial FEA software MSC/NASTRAN. From these analysis results, failure, safety factor and design validity are assessed. These results can be successfully applicable as reference data when a new satellite is developed as well as giving out an excellent criteria in satellite vibration treatment design.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2634-2636
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• 2004

다목적실용위성2호의 위성 본체시스템에는 지상과 연락을 담당하는 주 컴퓨터인 OBC, 위성의 자세를 제어를 위한 원격구동장치인 RDU 그리고 위성의 전원분배를 제어장치인 ECU인 3개의 동일 프로세서(386)가 탑재되어 각 담당 임무를 수행하는 분산형 구조를 갖고 있다. 각 프로세서는 EEPROM과 SRAM 데이터 메모리를 갖고 있는데 전원 리셋이 일어나면 모든 프로그램은 EEPROM에서 SRAM으로 복사되어 운영 프로그램이 실행하도록 되어 있다. 그러나 SRAM은 우주환경에서 위성체는 방사선에 노출되어 손상을 입을 때 SEU이 발생되어 정보가 왜곡되거나 상실되는 문제를 갖고 있다. 그러므로 본 논문에서는 변형된 해밍코드 기법을 이용하여 데이터를 수신하는 곳에서 에러를 검출 및 수정하는 디지털 회로 설계방법을 기술하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.83-86
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• 2004

Likewise all that of the propulsion system, development of Propulsion System for LEO Satellite is laborous tasks to surmount technical barriers of the advanced countries as well as to satisfy the requirements of evolving satellites and changes of functions, structures and etc. Those will be presented and discussed here that the process of technical approach to have developed the KOMPSAT propulsion system, and some challenging area to overcome to develop future LEO satellite propulsion system.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.29 no.2 s.233
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• pp.262-269
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• 2005

Optimization of a satellite structure under severe space launching environments is performed considering various design constraints. Simulate annealing, one of combinatorial optimization techniques, is used to optimize the satellite. The optimization results by the simulated annealing are compared to those by the method of modified feasible direction and genetic algorithm. Ten bar truss structure is optimized for feasibility study of the simulated annealing. Finally, the satellite structure is optimized by the simulated annealing algorithm under space environment. Weights of the satellite upper platform and propulsion module are minimized with consideration of several static and dynamic constraints. MSC/NASTRAN is used to find the static and dynamic responses. Simulated annealing has been programmed and integrated with the finite element analysis program for optimization. It is shown that the simulated annealing algorithm can be extended to the optimization of space structures.

• Journal of Satellite, Information and Communications
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• v.12 no.1
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• pp.132-136
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• 2017

In this paper, expanded lowest operating frequency by adopting circular slot on ground of balun and balance improved balance performances by stacking dielectric layer balun is proposed. Bandwidth of proposed balun is 1~7 GHz, and electrical length is $0.05{\lambda}$ at 1 GHz. In order to check performances of the proposed balun, simple dipole is integrated with the balun and radiation pattern of dipole is measured.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.68-75
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• 2008

Space radiation environments depend on satellite mission orbit, period, and date, and it can be predicted by simulation. Total Ionizing Dose(TID) can be predicted by Dose-depth Curve which only inform the dose level depending on the shielding thickness. So detail effective shielding analysis considering real structure is necessary to predict part level TID. For this purpose, program is developed to calculate shielding thickness distribution by structure modeling and ray trace from certain point in the structure. Finally TID at certain point in the 3-dimensional structure can be calculated by integration of shielding distribution result and dose-depth curve data. Using this program, TID is analyzed at part level certain point by modeling of equipment box structure in the satellite.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.155-164
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• 2002

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.76-83
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• 2006

Space radiation environment for COMS is simulated by NASA AP8/AE8, JPL91 and NRL CREME models, respectively for trapped particle, solar proton and cosmic-ray. The radiation effects on electronic devices in communication payload are also estimated by using simulation results. Dose-depth curve and LET spectrum are calculated for estimating total ionizing dose(TID) effect and single event effect(SEE) respectively. Spherical sector method is applied to dose estimation at each position in the units of communication payload to consider shielding effect of platform and housing. Total ionizing dose at each position varies by 8 times through shielding effect under the same external space radiation environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.833-839
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• 2013

Thermal vacuum test should be performed prior to launch to verify satellites' functionality in a harsh space environment which is represented by extremely cold temperatures and vacuum conditions. A thermal vacuum chamber which consists of a vacuum vessel, a pumping system, and a thermal control system are used to perform thermal vacuum tests of a satellite system and its components. A cryogenic blower is a core component of the closed loop thermal control system for thermal vacuum chambers. This paper describes the fan design of the cryogenic blower, the design of the thermal protection interface between the driving part and the fluid part, which were verified by thermal and structural analyses. The performance of the cryogenic blower is confirmed by similarity test on the test bench.