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논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 박설현
- 발행연도
- 2019
- 저작권
- 조선대학교 논문은 저작권에 의해 보호받습니다.
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Recently, the use of a variety of cubesatellites in the space industry has been receiving increased attention. A systematic structural design and analysis are required to effectively integrate avionics and payloads into the cubesatellite and protect them from launch and space environments. In this study, the structural design for the Korea Microgravity Science Laboratory (KMSL) cubesatellite were described followed by structural analysis.
To build and implement a robust structure for the KMSL cubesatellite, quasi-static and random vibration analyses were numerically conducted by following the GSFC-STD-7000 regulations which are similar to that of the Falcon 9. The predicted natural frequency of the designed structure for the KMSL cubesatellite was greater than the resonance frequency of the Falcon 9 launch vehicle. Additionally, the robustness of the structure was confirmed by the numerical results obtained from the quasi-static and random vibration analyses.
In this study a series of vibration experiments were additionally conducted to confirmed the robustness of the KSML cubesatellite. The vibration experiments performed in the study includes Low Level Sine Sweep, Sine Vibration, Random Vibration and Sine Burst (Quasi-Static). Through the LLSS and Sine Vibration experiments, the natural frequencies of the Cube satellites were determined, and random vibrations and sine bursts were used to determine the robustness of a satellites against vibrations and impacts. The structural safety of the cube satellite designed and fabricated finally was verified by comparing to results obtained from to numerical analysis.
To build and implement a robust structure for the KMSL cubesatellite, quasi-static and random vibration analyses were numerically conducted by following the GSFC-STD-7000 regulations which are similar to that of the Falcon 9. The predicted natural frequency of the designed structure for the KMSL cubesatellite was greater than the resonance frequency of the Falcon 9 launch vehicle. Additionally, the robustness of the structure was confirmed by the numerical results obtained from the quasi-static and random vibration analyses.
In this study a series of vibration experiments were additionally conducted to confirmed the robustness of the KSML cubesatellite. The vibration experiments performed in the study includes Low Level Sine Sweep, Sine Vibration, Random Vibration and Sine Burst (Quasi-Static). Through the LLSS and Sine Vibration experiments, the natural frequencies of the Cube satellites were determined, and random vibrations and sine bursts were used to determine the robustness of a satellites against vibrations and impacts. The structural safety of the cube satellite designed and fabricated finally was verified by comparing to results obtained from to numerical analysis.
목차
LIST OF TABLES ⅠLIST OF FIGURES ⅡNOMENCLATURE ⅣABSTRACT Ⅵ제 1장 서 론 11.1 연구 배경 및 필요성 11.2 연구 목적 및 내용 6제 2장 구조해석 이론 92.1 유한요소를 이용한 구조해석 이론 92.2 준정적해석(Quasi-Static Analysis) 이론 122.3 모드해석(Modal Analysis) 이론 142.4 랜덤진동해석(Random Vibration Analysis) 이론 17제 3장 KMSL 큐브위성의 구조설계 및 해석 193.1 과학 탑재체의 하우징 설계 및 구조해석 193.2 큐브위성 설계 요구사항 및 형상 설계 263.3 준정적해석(Quasi-Static Analysis) 결과 343.4 모드해석(Modal Analysis) 및 랜덤진동해석(Random VibrationAnalysis) 결과 42제 4장 진동 시험 결과 50제 5장 결 론 63【참고문헌】 6
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