Material Properties Evolution Affecting Demisability for Space Debris Mitigation
Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 32845
Material Properties Evolution Affecting Demisability for Space Debris Mitigation

Authors: Chetan Mahawar, Sarath Chandran, Sridhar Panigrahi, V. P. Shaji

Abstract:

The ever-growing advancement in space exploration has led to an alarming concern for space debris removal as it restricts further launch operations and adventurous space missions; hence various technologies and methods are explored for re-entry predictions and material selection processes for mitigating space debris. The selection of material and operating conditions is determined with the objective of lightweight structure and ability to demise faster subject to spacecraft survivability during its mission. The various evolving thermal material properties such as emissivity, specific heat capacity, thermal conductivity, radiation intensity, etc. affect demisability of spacecraft. Thus, this paper presents the analysis of evolving thermal material properties of spacecraft, which affect the demisability process and thus estimate demise time using the demisability model by incorporating evolving thermal properties for sensible heating followed by the complete or partial break-up of spacecraft. The demisability analysis thus concludes that the best suitable spacecraft material is based on the least estimated demise time, which fulfills the criteria of design-for-survivability and as well as of design-for-demisability.

Keywords: Demisability, emissivity, lightweight, re-entry, survivability.

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 268

References:


[1] IADC, "Inter-Agency Space debris Coordination Committee," 2011.
[2] D. R. Chapman, "An analysis of the corridor and guidance requirements for supercircular entry into planetary atmosphere," National Aeronautics and Space Administration, pp. 1-49, 1960.
[3] N. X. Busemann, R. D. Culp and e. a. Vinh, Hypersonic and planetary entry flight mechanics, Ann Arbor: University of Michigan Press, 1980.
[4] T. Mirko and H. G. Lewis, "Re-entry prediction and demisability analysis for atmospheric disposal," Advances in Space research, vol. 68, p. 15, Oct. 2021.
[5] G. I. Barsoum, H. H. Ibrahim and M. A. Fawzy, "Static and Random Vibration Analyses of a University CubeSat Project," Journal of Physics: Conference series, p. 13, 2019.
[6] "European Cooperation for Space Standardization, Structural general requirements," ECSS Stnd., 2008.
[7] A. C. Okolie, S. O. Onuh, Y. T. Olatunbosun and M. S. Abolarin, "Design optimization of Pico-satellite frame for computational analysis and simulation," Am. J. Mech. Ind. Eng. 1, pp. 74-84, 2016.
[8] S. J. Kang and H. U. Oh, "On orbit thermal design and validation of 1 U standardized cubesat of step cube," International Journal of Aerospace engineering, pp. 1-17, 2016.
[9] J. Piattoni, G. P. Candini and G. Pezzi, "Plastic Cubesat: An innovative and low-cost way to perform applied space research and hands-on education," Acta Astronaut, p. 10, 2012.
[10] T. Lips, V. Watermann and G. Koppenwallner, "Comparison of ORSAT and SCARAB re-entry survival results.," in European Conf. on Space Debris, Darmstadt.
[11] X. He and X. Zuo, "Surrogate-based entire trajectory optimization for full space mission from launch to re-entry.," Acta Astronautica, vol. 190, p. 20, 2021.
[12] T. Mirko, H. G. Lewis and C. Camilla, "Spacecraft design optimisation for demise and survivability," Aerospace Science and Technology, p. 20, Oct. 2018.
[13] J. Beck and Holbrough, "Belstead Research (Online)," Jan 2015. (Online), Available: http://www.belstead.com.
[14] A. Tewari, Atmospheric and Space Flight Dynamics: Modeling and Simulation with MATLABĀ® and SimulinkĀ®, Birkhcauser, 2007.
[15] M. Trisolini and H. G. Lewis, "Demisability and survivability sensitivity to design-for-demise techniques.," Acta Astronautica, p. 28, Jan. 2018.
[16] E. A. Slejko, A. Gregorio and V. Lughi, "Material selection for a CubeSat structural bus complying with debris mitigation.," Advances in Space research, p. 9, Dec. 2020.
[17] R. L. Kelley and D. R. Jarkey, "CubeSat material limits for Design for Demise," Space Conferences and Exposition, p. 4, 2015.
[18] J. J. Valencia and P. N. Quested, "Thermophysical properties," ASM Handbook.
[19] MatWeb, "L. L. C. MatWeb," 2022.