Performance Optimization of a Straight-Scheme Hybrid Rocket Motor
V. A. Arkhipov1, S. S. Bondarchuk2, A. S. Zhukov1, N. N. Zolotarev1, K. G. Perfil'eva1
1Tomsk State University, Tomsk, 634050 Russia
2Institute for Problems of Chemical and Energetic Technologies,Siberian Branch, Russian Academy of Sciences, Biisk, 659322 Russia
Keywords: гибридный ракетный двигатель, твердотопливный заряд, дополнительный окислительный компонент, скорость горения, полнота сгорания, hybrid rocket motor, solid propellant charge, additional oxidizer, burning rate, combustion efficiency
Abstract
A method for performance optimization of a straight-scheme hybrid rocket motor is considered. The method is based on inserting an additional amount of an oxidizer into the solid propellant with a prescribed distribution of the oxidizer mass fraction along the solid propellant charge. An analytical dependence is derived for the oxidizer fraction distribution that ensures uniform combustion and high efficiency of the solid propellant charge.
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