Structural Design and Analysis of an Advanced LEO EO Satellite/STM
- Paper number
IAC-08.C2.1.4
- Author
Dr. Jae Hyuk Lim, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Mr. Kyung-Won Kim, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Mr. Sun-Won Kim, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Dr. Juhun Rhee, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Dr. Do-Soon Hwang, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Dr. Ik-Min Jin, Korea Aerospace Research Institute, Korea, Republic of
- Coauthor
Dr. Hak Jung Kim, Korea Aerospace Research Institute, Korea, Republic of
- Year
2008
- Abstract
In this paper, the results of the structural design and analysis of an advanced LEO satellite of STM (Structural and Thermal Model) equipped with a high resolution camera are presented. To feature high agility in orbit, four high torque RWAs(Reaction Wheels Assemblies) are adopted. This enables to possess the power enough to change its attitude shortly. Also, the MOI(Moment of Inertia) of the structure is reduced as much as possible by making the structure compact. Three S/As(Solar Arrays) are mounted on the hexagonal shaped bus structure using stiff joints of hinges and struts, to meet the requirement of the fundamental deployed frequency of S/A. Struts are accommodated to support a heavy camera. To avoid a resonance between the bus structure and the launch vehicle at the launch stage, the fundamental frequency of all structures such as platforms and panels is designated to be higher than the requirement from the launch vehicle. To verify our satellite during launch using STM, several tests are performed such as sine burst test, sinusoidal vibration test, and acoustic test. And then a STM finite element model is tuned using the results of sinusoidal vibration test. Sine burst test apply a quasi-static load to the structure using a vibration shaker to verify the strength of primary structure members; Sinusoidal vibration test is to qualify the structure and subsystems for the low frequency sinusoidal transient loads; Acoustic test is to qualify the STM under the launch acoustic environment and the adequacy of the component random vibration level. In addition to these, separation shock test and S/A deployment test are performed. Results of coupled load analysis (CLA) using the tuned finite element model is assessed. Through comparisons of results between tests and analysis, several modifications have been made and will be applied to FM (Flight Model).
- Abstract document
- Manuscript document
IAC-08.C2.1.4.pdf (🔒 authorized access only).
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