Abstract The fuel regression rate is an important parameter in the design process of the hybrid rocket motor. Additives in the solid fuel may have influences on the fuel regression rate, which will affect the internal ballistics of the motor. A series of firing experiments have been conducted on lab-scale hybrid rocket motors with 98% hydrogen peroxide (H2O2) oxidizer and hydroxyl terminated polybutadiene (HTPB) based fuels in this paper. An innovative fuel regression rate analysis method is established to diminish the errors caused by start and tailing stages in a short time firing test. The effects of the metal Mg, Al, aromatic hydrocarbon anthracene (C14H10), and carbon black (C) on the fuel regression rate are investigated. The fuel regression rate formulas of different fuel components are fitted according to the experiment data. The results indicate that the influence of C14H10 on the fuel regression rate of HTPB is not evident. However, the metal additives in the HTPB fuel can increase the fuel regression rate significantly.
Highlights An innovative fuel regression rate analysis method is established. Fuel regression rates of 98% H2O2 and HTPB based fuels are fitted. Influence of C14H10 to the fuel regression rate of HTPB is not evident. Metal additives can improve the fuel regression rate of HTPB based fuel.
Experimental investigation of fuel regression rate in a HTPB based lab-scale hybrid rocket motor
Acta Astronautica ; 105 , 1 ; 95-100
2014-08-29
6 pages
Article (Journal)
Electronic Resource
English
Experimental investigation of fuel regression rate in a HTPB based lab-scale hybrid rocket motor
Online Contents | 2014
|Regression rate behaviors of HTPB-based propellant combinations for hybrid rocket motor
Online Contents | 2016
|