Optimal Design of a High-Agility Satellite with Composite Solar Panels

다국어 초록 (Multilingual Abstract)

This paper defines mode shape function of a composite solar panel assumed as Kirchhoff-Love plate for considering a torsional mode of composite solar panel. It then goes on to define dynamic model of a high-agility satellite considering the flexibility of composite solar panel as well as stiffness of a solar panel’s hinge using Lagrange’s theorem, Ritz method and the mode shape function. Furthermore, this paper verifies the validity of dynamic model by comparing numerical results from the finite element analysis. In addition, this paper performs a dynamic response analysis of a rigid satellite which includes only natural modes for solar panel’s hinges and a flexible satellite which includes not only natural modes of solar panel’s hinges, but also structural modes of composite solar panels. According to the results, we confirm that the torsional mode of solar panel should be considered for the structural design of high-agility satellite. Finally, we performed optimization of high-agility satellite for minimizing mass with solar panel’s area limit using the defined dynamic model. Consequently, we observed that the defined dynamic model for a high-agility satellite and result of the optimal design are very useful not only because of their optimal structural design but also because of the dynamic analysis of the satellite.

참고문헌 (Reference)

1 김대관, "태양전지판의 유연 모드를 고려한 위성의 동적 모델링" 한국항공우주학회 37 (37): 837-842, 2009

2 Arthur, W. L., "Vibrations of Continuous Systems" McGraw-Hill Companies 2011

3 Reddy, J. N., "Theory and Analysis of Elastic Plates and Shells" CRC Press 2007

4 Scrivener, S. L., "Survey of Time Optimal Attitude Maneuvers" 17 (17): 225-233, 1994

5 Thomas, P. S., "Spacecraft Structures and Mechanisms from Concept to Launch" 1995

6 Malekzadeh, M., "Robust Control of Non-linear Flexible Spacecraft" 17 (17): 217-228, 2010

7 Liu, J., "Rigid-Flexible-Thermal Coupling Dynamic Formulation for Satellite and Plate Multibody System" 52 : 102-114, 2016

8 Lim, J. H., "Recent Trend of the Configuration Design of High Resolution Earth Observation Satellites" 8 : 45-54, 2010

9 Byers, R. M., "Quasi Closed Form Solution to the Time Optimal Rigid Spacecraft Reorientation Problem" 16 (16): 453-461, 1993

10 Sedighi, M, "On the static and dynamic analysis of a small satellite" 52 (52): 1007-1012, 2003

11 Li, F., "Numerical Approach for Solving Rigid Spacecraft Minimum Time Attitude Maneuvers" 13 (13): 38-45, 1997

12 Bai, Z., "Modal Analysis for Small Satellite System with Finite Element Method" IEEE 1-5, 2008

13 Ebarahimi, A., "Minimum-Time Optimal Control of Flexible Spacecraft for Rotational Maneuvering" 2004

14 Tsai, S. W., "Introduction to Composite Materials" TECHNOMIC 1980

15 Goldberg, D. E., "Genetic Algorithms in Search, Optimization, and Machine Learning" Pearson Education 2013

16 Hu, Q. L., "Flexible Spacecraft Vibration Suppression Using PWPF Modulated Input Component Command and Sliding Mode Control" 9 (9): 20-29, 2007

17 Daniel, J. I., "Engineering Vibration" Pearson International Edition 2007

18 He, W., "Dynamic Modeling and Vibration Control of a Flexible Satellite" 51 (51): 1422-1431, 2015

19 Meng, J., "Dynamic Modeling and Simulation of Tethered Stratospheric Satellite with Thermal Effects" 110 : 181-189, 2016

20 Augustynek, K., "Dynamic Analysis of a Satellite with Flexible Links" LVI (LVI): 199-208, 2009

21 Hwang, D. S., "Design and Analysis of Satellite Structure" 27 (27): 111-121, 1999

22 Holland, J. H., "Adaptation in Natural and Artificial System" University of Michigan Press 1975