Design of an energy absorption system for the landing of space exploration modules

Authors

  • Quirino Estrada-Barbosa Instituto de Ingeniería y Tecnología https://orcid.org/0000-0003-0623-3780
  • Eladio Martínez-Rayón Centro Nacional de Investigación y Desarrollo Tecnológico CENIDET/TecNM, Interior Internado Palmira S/N, Col. Palmira, C.P. 62490, Cuernavaca, Morelos, México https://orcid.org/0000-0003-3846-6888
  • Elva Lilia Reynoso-Jardón Instituto de Ingeniería y Tecnología https://orcid.org/0000-0002-0729-2822
  • Jesús Silva-Aceves Instituto de Ingeniería y Tecnología, Universidad Autónoma de Ciudad Juárez, Ciudad Juárez, Chihuahua, México
  • Manuel de Jesús Nandayapa-Alfaro Instituto de Ingeniería y Tecnología https://orcid.org/0000-0002-5928-9561
  • Lara C. Wiebe Instituto de Ingeniería y Tecnología, Universidad Autónoma de Ciudad Juárez, Ciudad Juárez, Chihuahua, México https://orcid.org/0000-0002-6336-0885
  • Francisco Javier Enríquez-Aguilera Instituto de Ingeniería y Tecnología https://orcid.org/0000-0003-4716-1138

DOI:

https://doi.org/10.37636/recit.v7n2e345

Keywords:

Thin-walled structure, Space exploration, Finite element method, Energy absorption system

Abstract

Currently, space exploration is becoming an increasingly important activity since it allows increased knowledge regarding the formation of planets, economic activities (space mining) as well as a better understanding of geological and biological phenomena that allow the creation of space in the future of human habitats outside planet Earth. In this sense, one of the main problems of space exploration is associated with the safe landing of space probes. Based on the above, this article proposes the design of a passive type of energy absorption system based on plastic deformation of aluminum structural profiles. For this purpose, structural profiles with various geometric shapes were individually designed and evaluated using the Abaqus finite element software. The numerical evaluation was carried out through compression tests in conjunction with the calculation of the main impact resistance parameters. The results showed a better performance of the HSC-1 profile which obtained the best crushing force efficiency (CH-C) equal to 0.83. From the above, it was implemented in a discrete model of a generic space lander.

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Generalities of the discrete model of the energy absorption system applied to the landing system of a generic module.

Published

2024-04-15

How to Cite

Estrada-Barbosa , Q., Martínez-Rayón, E., Reynoso-Jardón, E. L., Silva-Aceves, J., Nandayapa-Alfaro, M. de J., Wiebe, L. C., & Enríquez-Aguilera, F. J. (2024). Design of an energy absorption system for the landing of space exploration modules. REVISTA DE CIENCIAS TECNOLÓGICAS (RECIT), 7(2), e345. https://doi.org/10.37636/recit.v7n2e345

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