Design and simulation Sandwich Composite Fairing Shells Using FEM Analyzing

Document Type : Research Paper

Authors

1 Department of Aerospace engineering, Malek Ashtar University of Technology, Tehran, Iran

2 Polymer Engineering Department, Amirkabir University of Technology, Tehran, Iran

3 Composite Materials Department, Materials & Manufacturing Technology Faculty, Malek Ashtar University of Technology, Tehran, Iran

4 Department of Chemical Engineering, Faculty of Engineering, University of Isfahan, Isfahan, Iran

Abstract

   In order to investigate and improve the destructive effects of maneuvers that the flying body has during a flight in space, it is necessary to know the forces acting on the flying body. In this paper, an analysis of the composite sandwich structure of a launch vehicle fairing is considered. This study explores carbon-fiber-reinforced skins with different cores used to deploy satellites and can be used as a space habitat. In order to calculate the effective forces on sandwich skins, finite element method (FEM) was used to determine three-dimensional stress and strain. Three types of structural models with honeycomb and solid core under dynamic loads were compared and evaluated. Models were compared in three category of stress distribution, strain and weight. The honeycomb core pattern helps reduce the structure's weight up to half of the structure compared to a solid core. The effect of mesh size sensitivity applied on simulations. The results showed that the amount of stress and strain were the same in all models and only differed in dispersion. However, the composite sandwich structure with aluminum core showed more strength against the applied forces.

Keywords

[1]           A. Çekiç, Improvement of finite element model by using sine vibration test results of acommunication satellite,  Thesis, Middle East Technical University, 2021.
[2]           S. A. Astakhov, V. I. Biryukov, Buckling under the action of loading by aerodynamic and inertial forces during ground track tests of aviation equipment, INCAS Bulletin, Vol. 13, pp. 5-12, 2021.
[3]           C. Merrem, V. Wartemann, T. Eggers, Preliminary aerodynamic design of a reusable booster flight experiment, CEAS Space Journal, Vol. 12, No. 3, pp. 429-439, 2020.
[4]           R. Mehta, Estimation of Angle of Attack in Satellite Launch Vehicle Using Flush Air Data Sensing Systems at Mach 0.5 to 3.0, Sch J Eng Tech, Vol. 7, pp. 77-86, 2021.
[5]           J. Makhija, D. S. K. Reddy, Numerical simulation of flow field over slender bodies at transonic Mach number and low angle of attacks, in Proceeding of, IOP Publishing, pp. 042047.
[6]           M. Ozair, M. N. Qureshi, Numerical Prediction of Aeroacoustic Loads on a Hammerhead Nose Cone Configuration, in Proceeding of, IEEE, pp. 806-810.
[7]           P. Vitagliano, F. De Gregorio, P. Roncioni, F. Paglia, C. Milana, AERODYNAMIC CHARACTERISATION OF VEGA-C LAUNCHER.
[8]           P. Hao, Z. Li, S. Feng, W. Li, Y. Wang, B. Wang, A novel framework for reliability assessment of payload fairing separation considering multi-source uncertainties and multiple failure modes, Thin-Walled Structures, Vol. 160, pp. 107327, 2021.
[9]           S. G. Vincenzino, W. Rotärmel, I. Petkov, H. Elsäßer, E. Dumont, L. Witte, S. Schröder, Reusable structures for callisto, in Proceeding of.
[10]         F. Morovat, A. Mozaffari, J. Roshanian, H. Zare, A novel aspect of composite sandwich fairing structure optimization of a two-stage launch vehicle (Safir) using multidisciplinary design optimization independent subspace approach, Aerospace Science and Technology, Vol. 84, pp. 865-879, 2019.
[11]         D. Cui, J. Zhao, S. Yan, X. Guo, J. Li, Analysis of parameter sensitivity on dynamics of satellite separation, Acta Astronautica, Vol. 114, pp. 22-33, 2015.
[12]         C. E. Groves, Dissertation Defense Computational Fluid Dynamics Uncertainty Analysis for Payload Fairing Spacecraft Environmental Control Systems,  pp. 2014.
[13]         J. Roshanian, M. Ebrahimi, Latin hypercube sampling applied to reliability-based multidisciplinary design optimization of a launch vehicle, Aerospace Science and Technology, Vol. 28, No. 1, pp. 297-304, 2013.
[14]         X. Zhu, H. Li, T. Yu, B. Song, Research on reliability analysis for low-altitude and high-speed payload fairing separation, in Proceeding of, IEEE, pp. 90-94.
[15]         A. Gilioli, C. Sbarufatti, A. Manes, M. Giglio, Compression after impact test (CAI) on NOMEX™ honeycomb sandwich panels with thin aluminum skins, Composites Part B: Engineering, Vol. 67, pp. 313-325, 2014.
[16]         Y.-B. Park, J.-H. Kweon, J.-H. Choi, Failure characteristics of carbon/BMI-Nomex sandwich joints in various hygrothermal conditions, Composites Part B: Engineering, Vol. 60, pp. 213-221, 2014.
[17]         R. Roy, K. Nguyen, Y. Park, J. Kweon, J. Choi, Testing and modeling of Nomex™ honeycomb sandwich Panels with bolt insert, Composites Part B: Engineering, Vol. 56, pp. 762-769, 2014.
[18]         X. Xue, C. Zhang, W. Chen, M. Wu, J. Zhao, Study on the impact resistance of honeycomb sandwich structures under low-velocity/heavy mass, Composite Structures, Vol. 226, pp. 111223, 2019.
[19]         Z. Zhao, C. Liu, L. Sun, H. Luo, J. Wang, Y. Li, Experimental and numerical study on the constrained bending-induced collapse of hexagonal honeycomb, Composite Structures, Vol. 277, pp. 114604, 2021.
[20]         A. Karakoç, K. Santaoja, J. Freund, Simulation experiments on the effective in-plane compliance of the honeycomb materials, Composite Structures, Vol. 96, pp. 312-320, 2013.
[21]         R. Roy, S.-J. Park, J.-H. Kweon, J.-H. Choi, Characterization of Nomex honeycomb core constituent material mechanical properties, Composite Structures, Vol. 117, pp. 255-266, 2014.
[22]         J. Kratz, P. Hubert, Anisotropic air permeability in out-of-autoclave prepregs: Effect on honeycomb panel evacuation prior to cure, Composites Part A: Applied Science and Manufacturing, Vol. 49, pp. 179-191, 2013.
[23]         D. J. Sypeck, H. N. Wadley, Cellular metal truss core sandwich structures, Advanced Engineering Materials, Vol. 4, No. 10, pp. 759-764, 2002.
[24]         L. Liu, P. Meng, H. Wang, Z. Guan, The flatwise compressive properties of Nomex honeycomb core with debonding imperfections in the double cell wall, Composites Part B: Engineering, Vol. 76, pp. 122-132, 2015.
[25]         W. Wang, Y. Dai, C. Zhang, X. Gao, M. Zhao, Micromechanical modeling of fiber-reinforced composites with statistically equivalent random fiber distribution, Materials, Vol. 9, No. 8, pp. 624, 2016.
[26]         G. Di Mauro, M. Lawn, R. Bevilacqua, Survey on guidance navigation and control requirements for spacecraft formation-flying missions, Journal of Guidance, Control, and Dynamics, Vol. 41, No. 3, pp. 581-602, 2018.
Volume 53, Issue 1
March 2022
Pages 55-65
  • Receive Date: 28 November 2021
  • Revise Date: 07 February 2022
  • Accept Date: 25 February 2022
  • First Publish Date: 01 March 2022