Dynamics of manned spaceship fairing elements motion in emergency

Authors: Kokushkin V.V., Khomyakov M.K., Ovsyannikova N.Yu. Published: 14.02.2016
Published in issue: #1(106)/2016  

DOI: 10.18698/0236-3941-2016-1-4-16

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control  
Keywords: spaceship, reentry module, separated nose fairing, emergency abort, separation dynamics, interaction force

The paper considers separation processes related to manned spaceship crew escape in case of launch vehicle crash at the end of the atmospheric flight path. We carried out the research in two stages. The first one included nose separation from the launch vehicle. At the second stage the reentry module was detached from the nose. The calculations resulted in obtaining the vector field of the fairing state at the moment of reentry module separation. The vector field helped to investigate the reentry module separation from the fairing. The analysis of the reentry module separation revealed the possibility of the contact between its hull and the fairing elements. Mathematical model of contact interaction was proposed. We provide the calculation results of the reentry module separation and contact forces estimation.


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