Methodology for the Design of Combustible Structures of Separating Launch Vehicle Parts
Author:
Affiliation:
1. Omsk State Technical University, 644050, Omsk, Russia
2. Sobolev Institute of Mathematics, 630090, Novosibirsk, Russia
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.A34920
Reference15 articles.
1. Spacecraft re-entry strategies: Meeting debris mitigation and ground safety requirements
2. Spacecraft disintegration during uncontrolled atmospheric Re-entry
3. Entry Trajectory Model with Thermomechanical Breakup
4. A comparison of commonly used re-entry analysis tools
5. Aerothermodynamics calculation of thermal destruction of “Fregat” upper stage at descent in the Earth's atmosphere
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1. Mathematical modeling of disposal of the payload fairing of a launch vehicle after completion;VESTN TOMSK GOS U-MA;2023
2. Experimental studies of thermodynamic combustion processes of combustible demonstrators;Journal of Physics: Conference Series;2022-03-01
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