• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.32.1-32.1
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• 2011

이 논문에서는 저궤도 지구관측위성 비행모델의 정현파 가진시험 결과에 대하여 분석하였다. 정현파 가진시험은 발사환경시험중의 하나로서, 저주파 대역의 정현파 진동 환경하에서 인공위성의 안정성을 검증하는데 그 목적이 있다. 정현파 가진시험의 입력선도는 발사체로부터 선정되어진다. 발사체로부터 선정된 입력선도는 극한의 경우를 고려한 선도이므로 실제 정현파 가진시험시에는 입력선도에 적절한 노칭을 적용하여야 한다. 노칭은 주구조물의 대한 1차 노칭과 부가 구조물에 대한 2차 노칭으로 구분이 되어 적용되었다. 정현파 가진시험의 전후에는 저수준 정현파가진시험을 수행하였으며, 주파수 응답함수를 비교함으로서 구조적으로 문제가 없는지를 확인하였다. 시험 후, 육안검사를 통하여 구조 부재가 이상이 없는지를 최종 확인하였으며, 인공위성비행모델이 정현파 가진 환경하에서 충분히 안전함을 확인하였다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2005.05a
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• pp.966-970
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• 2005

On the basis of the development of KSLV-1, KoDSat was designed and manufactured to demonstrate the performance of KSLV-1. KoDSat is exposed to a severe vibrational environment at launch. The structural reliability of KoDSat has to be verified using vibrational test. The structural compatibility and verification of components between analysis and test can be proved using environmental vibration test. In this paper, we review the structural characteristic of thruster control unit for a space launch vehicle and design TCU housing using mathematical model. In order to verify the structural compatibility and reliability, half-sine shock, random and sing sweep vibration test was performed. Especially, sing sweep vibration test result is compared with analysis result and mathematical model is verified.

• Journal of Satellite, Information and Communications
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• v.5 no.1
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• pp.80-84
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• 2010

Satellite structure should be designed to accommodate and support safely the payload and equipments necessary for its own missions and to secure satellite and payloads from severe laucnch enviroments. The lauch environments imposed on satellites are quasi-static accelerations, aerodynamic loads, acoustic loads and shock loads. To qualify the structure design against low-frequency dyanmic enviromnent, sine vibration test should be performed. During sine vibration test, the notchings are implemented in order to keep the payloads and equipments from excessive loading at their own main modes. This paper deals with sine test prediction, sine vibration test results, comparison of predicted values and tested values, and verification of Finite Element Model.