AbstractThis paper presents transient simulations and experimental studies of the ignition process of the hybrid rocket motors (HRMs) using 90% hydrogen peroxide (HP) as the oxidizer and polymethyl methacrylate (PMMA) and Polyethylene (PE) as fuels. A fluid-solid coupling numerically method is established based on the conserved form of the three-dimensional unsteady Navier-Stokes (N-S) equations, considering gas fluid with chemical reactions and heat transfer between the fluid and solid region. Experiments are subsequently conducted using high-speed camera to record the ignition process. The flame propagation, chamber pressurizing process and average fuel regression rate of the numerical simulation results show good agreement with the experimental ones, which demonstrates the validity of the simulations in this study. The results also indicate that the flame propagation time is mainly affected by fluid dynamics and it increases with an increasing grain port area. The chamber pressurizing process begins when the flame propagation completes in the grain port. Furthermore, the chamber pressurizing time is about 4 times longer than the time of flame propagation.
HighlightsNumerical and experimental studies on ignition process are conducted.Ignition process of PMMA is recorded by high speed camera.Flame propagation time is mainly affected by fluid dynamics.Chamber pressuring time is about 4 times as long as flame propagation time.
Three-dimensional numerical and experimental studies on transient ignition of hybrid rocket motor
Acta Astronautica ; 140 ; 247-254
2017-08-20
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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