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한국생산제조학회 학술지 영문 홈페이지
[ Papers ]
Journal of the Korean Society of Manufacturing Technology Engineers - Vol. 28, No. 2, pp.93-99
ISSN: 2508-5107 (Online)
Print publication date 15 Apr 2019
Received 26 Mar 2019 Revised 11 Apr 2019 Accepted 12 Apr 2019
DOI: https://doi.org/10.7735/ksmte.2019.28.2.93

마이크로중력 과학미션 수행용 초소형위성의 구조체 설계와 해석

장정익a ; 박설현b, *
Structural Design and Analysis of Nanosatellite for Microgravity Scientific Missions
Jeong Ik Janga ; Seul Hyun Parkb, *
aDepartment of Mechanical System & Automotive Engineering, Graduate of Chosun University, 309, Pilmun-daero, Dong-gu, Gwangju 61452, Korea
bSchool of Mechanical System & Automotive Engineering, Chosun University, 309, Pilmun-daero Dong-gu, Gwangju 61452, Korea

Correspondence to: *Tel.: +82-62-230-7174 Fax: +82-62-230-7171 E-mail address: isaac@chosun.ac.kr (Seul Hyun Park).

Abstract

Recently, the use of nanosatellites in the space industry has been receiving increased attention. For the robust construction of a nanosatellite, the structure of the nanosatellite needs to be able to protect avionics and payloads from launch and space environments. In this study, we performed the structural design and analysis to build and implement a robust structure for the Korea Microgravity Science Laboratory nanosatellite. To this end, quasi-static and random vibration analyses were numerically conducted by applying a load of 18.75 G (specified by the GSFC-STD-7000 regulations) to the designed structure. The predicted natural frequency of the designed structure for the nanosatellite was greater than the resonance frequency of the launch vehicle. Additionally, the robustness of the structure was confirmed by the numerical results obtained from the quasi-static and random vibration analyses.

Keywords:

Nanosatellite, Cubesat, Structure, Quasi-static analysis, Modal analysis, Random vibration analysis

Acknowledgments

이 논문은 2019년도 정부(과학기술정보통신부)의 재원으로 한국연구재단의 지원을 받아 수행된 연구임(NO.NRF-2017M1A3A3A06016680, 큐브위성 경연대회 및 개발).

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