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Composite Sounding Rocket Payloads: A Structural Design Study


Title: Composite Sounding Rocket Payloads: A Structural Design Study

Authors: Florentius J. van Zanten, Wout De Backer

DOI: 10.33599/nasampe/c.22.0022

Abstract: The requirements for the structural properties of three different diameter sounding rockets are derived through (1) reverse analysis of an existing metal structure and (2) forward requirement analysis based on the flight loads. In the reverse analysis the stiffness, strength and failure loads for different failure mechanisms are determined. In the forward analysis two load cases are evaluated, the first is a pure take-off load case, while the second includes a drag-induced component as part of parabolic flight trajectory of the rocket.

Both analytical and finite element analyses are performed to determine the failure load of the metal sounding rocket, and used to size equivalent composite rocket structures accounting for typical composite failure modes. Based on these failure modes and the critical failure load, a compliant composite quasi-isotropic and a tailored laminate for the three different sounding rocket diameters are presented. For the tailored laminate, the laminate must be symmetric, and the design space is restricted to include only 45/-45/0/90 plies, this frees up additional design space.

For the quasi-isotropic structure, a mass savings of 44% is feasible while improving the sounding rocket failure load by a factor of 1.5. For the tailored laminates the mass savings are estimated to be 53%.

References: [1] J. H. S. Almeida, M. L. P. Tonatto, M. L. Ribeiro, V. Tita, and S. C. Amico, “Buckling and post-buckling of filament wound composite tubes under axial compression: Linear, nonlinear, damage and experimental analyses,” Composites Part B: Engineering, vol. 149, pp. 227–239, Sep. 2018, doi: 10.1016/J.COMPOSITESB.2018.05.004. [2] NASA, NASA Sounding Rockets User Handbook Sounding Rockets Program Office Sub-orbital and Special Orbital Projects Directorate, Wallops Island, NASA, 2015 [3] D. Gay, S. v. Hoa, and S. W. Tsai, Composite materials: Design and applications. CRC Press, 2002. [4] E. J. Barbero, Finite Element Analysis of Composite Materials using AbaqusTM. 2013. [5] P. Bala, A. V. Raviprakash, V. Ananthapathmanaban, “Parametric study on buckling behaviour of dented short carbon steel cylindrical shell subjected to uniform axial compression”, Thin-Walled Structures, Vol. 48, pp. 639-649, 2010, Doi:10.1016/j.tws. 2010.02.009. [6] D. O. Brush, B. O. Almroth, and J. W. Hutchinson, “Buckling of Bars, Plates, and Shells,” Journal of Applied Mechanics, 1975, doi: 10.1115/1.3423755. [7] E. J. Barbero, Introduction to Composite Materials Design. CRC Press, 1998. [8] R. Luciano and E. J. Barbero, “Formulas for the stiffness of composites with periodic microstructure,” International Journal of Solids and Structures, vol. 31, no. 21, pp. 2933–2944, 1994, doi: 10.1016/0020-7683(94)90060-4. [9] C. Kassapoglou, Design and Analysis of Composite Structures: With Applications to Aerospace Structures: Second Edition. 2013. doi: 10.1002/9781118536933. [10] M. P. Nemeth, “Simple Formulas and Results for Buckling- Resistance and Stiffness Design of Compression-Loaded Laminated-Composite Cylinders,” no. August, 2009. [11] NASA, “NASA SP-8007 Bucking of Thin Walled Circular Cylinders,” no. August, p. 60, 1968.

Conference: CAMX 2022

Publication Date: 2022/10/17

SKU: TP22-0000000022

Pages: 15

Price: $30.00

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