Thermo Elastic Analysis of a Type 3 Cryogenic Tank Considering Curing Temperature and Autofrettage Pressure

Abstract

In this study, effects of curing temperature and autofrettage pressure on a Type 3 cryogenic propellant tank, which is composed of composite hoop/helical layers and a metal liner, were investigated by thermo elastic analysis using finite element method. The temperature field of a Type 3 tank was obtained by solving the heat transfer problem and, in turn, was used as the nodal temperature boundary conditions during the elastic analyses for curing temperature and autofrettage pressure effects. Progressive failure analysis was also introduced in this procedure. As a result, it was shown that the higher the curing temperature was, the more residual compressive stress and tensile stress were induced in composites and metal liner, respectively. On the contrary, autofrettage pressure brought the reduction of these residual thermal stresses caused by cryogenic environments to the tank structure and these trends were verified from the composite/aluminum ring specimen tests at cryogenic temperature, which is suitable for preliminary tests of filament wound structures. This tradeoff for curing temperature and autoprettage pressure must be considered in the design and manufacturing stages for a Type 3 cryogenic tank.

Keywords

curing temperature autofrettage pressure cryogenic environment Type 3 tank thermo elastic analysis progressive failure analysis.

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References

Vendroux, G. , Auberon, M. and Dessaut, J. (1997). Cryogenic Composite Tanks: Structural Analysis and Manufacturing Concepts, 42nd Int SAMPE Symp., 42(2): 828—838.

Heydenreich, R. (1998). Cryotanks in Future Vehicles , Cryogenics, 38: 125—130.

Pasquier, A. , Peypoudat, V. and Prel, Y. (2002). Liquid Hydrogen Composite Tank for Two Stages to Orbit Reusable Launch Vehicle, 23rd Int. Symp. Space Technol. Sci., 23(1): 472—477.

Grimsley, B.W. , Cano, R.J. , Johnson , N.J. , Loos, A.C. and McMahon, W.M. (2001). Hybrid Composites for LH2 Fuel Tank Structure, Int. SAMPE Tech. Conf. Ser., 33: 1224—1235.

Whitley, K.S. and Gates, T.S. (2002). Thermal/Mechanical Response and Damage Growth in Polymeric Composites at Cryogenic Temperatures, Structures, Structural Dynamics, and Materials Conference (10th AIAA/ASME/ASCE/AHS adaptive structures forum, 4th AIAA nondeterministic approaches forum, 3rd AIAA gossamer spacecraft forum), pp. 1677—1689.

Shimoda, T. , Morino, Y. , Ishikawa, T. , Morimoto, T. and Cantoni, S. (2001). Study of CFRP Application to Cryogenic Fuel Tank for RLV, Proc. Jpn Int SAMPE Symp., 7: 275—278.

Scholliers, J. and Brussel, H.V. (1994). Computer-integrated Filament Winding: Computer-integrated Design, Robotic Filament Winding and Robotic Quality Control, Compos. Manuf., 5(1): 15—23.

Doh, Y.D. and Hong, C.S. (1995). Progressive Failure Analysis for Filament Wound Pressure Vessel, J. Reinf. Plast. Comp., 14(12): 1278—1306.

ABAQUS/Standard User's Manual, Hibbitt, Karlsson & Sorensen, Inc.

10.

Chang, F.K. (1987). A Progressive Damage Model for Laminated Composites Containing Stress Concentrations, J. Compos. Mater., 21: 834—851.

11.

Kim, C.U. (2004). Optimal Design of Axisymmetric Filament Wound Structures Based on Semi-Geodesic Path Algorithm, Ph.D. Thesis (KAIST).

12.

Kim, M.G. , Kang, S.G. , Kim , C.G. and Kong, C.W. (2004). A Study on Tensile Properties of CFRP Composites under Cryogenic Environment , J. Korean Soc. Compos. Mater., 17(6): 52—57.

13.

Kang, S.G. , Kim, M.G. and Kim, C.G. (2007). Evaluation of Cryogenic Performance of Adhesives using Composite-aluminum Double Lap Joints, Compos. Struct ., 78(3): 440—446.

14.

Incropera, F.P. and DeWitt, D.P. (1996). Fundamentals of Heat and Mass Transfer, John Wiley & Sons, New York, USA.

15.

Tompkins, S.S. (1987). Thermal Expansion of Selected Graphite-Reinforced Polymide-, Epoxy-, and Glass-Matrix Composites, Int. J. Thermophys, 8(1): 119—132.

16.

Yoon, S.H. , Cho, W.M. and Kim, C.G. ( 1997). Measurement of Tensile Properties using Filament Wound Ring Specimens, J. Reinf. Plast. Comp., 16(9): 810—824.