Abstract: The stowing and deploying experiment was
conducted for three 700 mm long thin-walled tubes, and the
structural behavior characteristics parameters were measured
clearly, including strain, deformation and wrapping moment. 3D
finite element models (FEM) were built subsequently and explicit
dynamic method was used to simulate the stowing and deploying of the
lenticular carbon fiber reinforced polymer (CFRP) thin-walled
tubular space boom, which was designed as four-ply
(45/-45/45/-45) lay-up. The stress
and energy during the wrapping process were got and compared with
different wrapping angular velocity, the reasonable wrapping angular
velocity and effective method were conformed, and structural
behavior characteristics were obtained. The results were compared
and discussed as well, and the results show that the numerical
results by 0.628 rad/s velocity agree well with the measured values.
In this paper, the numerical procedure and experimental results are
valuable to the optimization design of CFRP thin-walled tubular
space boom and future research.
LI Rui-xiong (李瑞雄), CHEN Wu-jun (陈务军), FU Gong-yi (付功义)
. Experimental and Stowing/Deploying Dynamical Simulation of Lenticular Carbon Fiber Reinforced Polymer Thin-Walled Tubular Space Boom[J]. Journal of Shanghai Jiaotong University(Science), 2012
, 17(1)
: 58
-064
.
DOI: 10.1007/s12204-012-1230-z
1 Chen Wu-jun. Deployable space structures and analysis theory [M]. Beijing: China Astronautics Press, 2006: 1-60 (in Chinese).
2 Kalamkarov A L, Georgiades A V, Rokkam S K, et al. Analytical and
numerical techniques to predict carbon nanotubes properties [J].
Solids and Structures, 2006, 43(2): 6832-6854.
3 Salama M, Kuo C P, Lou M. Simulation of deployment dynamics of
inflatable structures [J]. AIAA Journal, 2000, 38(12):
2277-2283.
4 Murphey T W. Historical perspectives on the development of
deployable reflectors [C]// 50th AIAA/ ASME/ ASCE/ AHS/ ASC
Structures, Structural Dynamics, and Materials Conference. Palm
Springs, California: American Institute of Aeronautics and
Astronautics, 2009: 1-28.
5 Gan W W, Pellegrino S A. Numerical approach to the kinematic
analysis of deployable structures forming a closed loop [J].
Mechanical Engineering Science, 2006, 220(7): 1045-1056.
6 Leipold M, Runge H, Sickinger C. Large SAR membrane antennas with
light weight deployable booms [C]// 28th ESA Antenna Workshop
on Space Antenna Systems and Technologies. Noordwijk, Netherlands:
American Institute of Aeronautics and Astronautics, 2005: 154-159.
7 Sickinger C, Herbeck L, Breitbach E. Structural engineering on
deployable CFRP booms for a solar propelled sailcraft [J]. Acta
Astronautica, 2006, 58(3): 185-196.
8 Ge Dong-ming, Chen Wu-jun. Coil buckling mechanism and structural
dynamical analysis for coilable extendable/retractable space masts
[D]. Shanghai: School of Naval Architecture, Ocean and Civil
Engineering, Shanghai Jiaotong University, 2007.
9 Li Rui-xiong, Chen Wu-jun, Fu Gong-yi, et al. Numerical simulation for flattening
and wrapping process of lenticular wrapped-rib [J]. Journal of
Astronautics, 2011, 32(1): 224-231 (in Chinese).
10 Li Rui-xiong, Chen Wu-jun, Fu Gong-yi, et al. Experiments and mechanical behavior
of wrapping process of lenticular wrapped-rib [J]. Engineering
Mechanics, 2011, 28(11): 244-250 (in Chinese).
11 Di Jie-jian, Duan Bao-yan. Preloading optimization of large
net-shape deployable antennas [J]. Journal of South China
University of Technology: Natural Science Edition, 2004,
32(6): 23-26 (in Chinese).
12 Wang Chang-guo, Du Xing-wen. Internal gas mass loss analysis of
inflatable space antenna reflector subjected to impact [J].
Journal of Harbin Institute of Technology, 2006, 38(4):
507-509 (in Chinese).
13 Liu Xiao-feng, Tan Hui-feng. Inflatable space structures and
deployment simulation [J]. Journal of Harbin Institute of
Technology, 2004, 36(4): 508-512 (in Chinese).
14 Wang J T, Chen T, Sleight D W, et al． Simulating nonlinear
deformations of solar sail membranes using explicit time integration
[C]// 45th AIAA/ASME /ASCE /AHS /ASC Structures,
Structural Dynamics and Materials Conference. Palm Springs,
California: American Institute of Aeronautics and Astronautics,
2004, 580-595.
