Space Debris Damaging of C/C-based Spacecraft Structures: Thermo-Mechanical Analysis of Impact Energy Effect in Ground Simulation by Railgun Ballistic Test
- Paper number
IAC-19,C2,6,9,x52026
- Author
Dr. Andrea Delfini, Italy, Sapienza University of Rome
- Coauthor
Dr. Roberto Pastore, Italy, Sapienza University of Rome
- Coauthor
Dr. Marta Albano, Italy, Agenzia Spaziale Italiana (ASI)
- Coauthor
Prof. Fabio Santoni, Italy, Sapienza University of Rome
- Coauthor
Prof. Mario Marchetti, Italy, Sapienza University of Rome
- Coauthor
Dr. Antonio Vricella, Italy, Sapienza University of Rome
- Year
2019
- Abstract
The long-standing problem of space debris requires to develop ever more reliable analysis systems, in order to achieve a suitable level of safe operating conditions in space manned activities. In this framework, the study of spacecraft outer surface resistance to hypervelocity impact is mandatory, since the ability of a material or a structure to withstand impacts of micrometeoroids and orbital debris (MMOD) may be crucial to guarantee the mission compliance with the low earth orbit (LEO) space environment. In this work, a thermo-mechanical characterization is carried out on Carbon/Carbon (C/C) plate-shaped structures by means of thermal expansion coefficient (CTE) measurements before and after impact testing, near the crater region and around plate boundary. The ballistic stage is performed by means of a linear electromagnetic accelerator system – developed in the so called ‘railgun’ configuration – and is discussed and compared to numerical FEM simulation results. The adopted experimental set-up proved to be suitable to perform impact testing of materials in the space debris energy range, allowing to assess the effect of different bump conditions on the impacted materials degradation.
- Abstract document
- Manuscript document
(absent)