Dynamic of Emergency Fairing Separation from Launch Vehicle in Atmospheric Ascent

The purpose of the article was to examine dynamics of the emergency separation of the fairing along with the spacecraft "Soyuz" reentry module during the rocket atmospheric ascent. The study suggests different mathematical models of variable mass body - separate fairing. First, we chose the optimal model allowing us to perform end-to-end simulation from fairing separation to reentry module self-contained motion. Then, we assessed noncollision of fairing separation from the launch vehicle, recorded the separation process and examined the fairing self-contained motion. Next, we found the regularities of the transient process and determined the fairing flow stability rating. Finally, we made a statistic analysis of the fairing self-contained motion.

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