Geometric effects of fuel regression rate in hybrid rocket motors

作     者：CAI GuoBiao ZHANG YuanJun WANG PengFei HUI Tian ZHAO Sheng YU NanJia 

作者机构：School of Astronautics Beihang University Beijing 100191 China Beijing Institute of Aerospace Systems Engineering Beijing 100076 China 

出 版 物：《Science China(Technological Sciences)》 (中国科学（技术科学英文版）)

年 卷 期：2016年第59卷第5期

页      面：807-813页

核心收录：

学科分类：0810[工学-信息与通信工程] 080703[工学-动力机械及工程] 08[工学] 082502[工学-航空宇航推进理论与工程] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0825[工学-航空宇航科学与技术] 0702[理学-物理学] 0812[工学-计算机科学与技术（可授工学、理学学位）] 

基　　金：supported by the Innovation Foundation of Beihang University for Ph.D.Graduates by the National Natural Science Foundation of China(Grant No.51206007) 

主　　题：geometric effect regression rate hydraulic diameter hybrid rocket motor 

摘      要：The geometric configuration of the solid fuel is a key parameter affecting the fuel regression rate in hybrid rocket motors. In this paper, a semi-empirical regression rate model is developed to investigate the geometric effect on the fuel regression rate by incorporating the hydraulic diameter into the classical model. The semi-empirical model indicates that the fuel regression rate decreases with increasing hydraulic diameter and is proportional to dh?0.2 when convective heat transfer is dominant. Then a numerical model considering turbulence, combustion, solid fuel pyrolysis, and a solid–gas coupling model is established to further investigate the geometric effect. Eight motors with different solid fuel grains are simulated, and four methods of scaling the regression rate between different solid fuel grains are compared. The results indicate that the solid fuel regression rates are approximate the same when the hydraulic diameters are equal. The numerical results verify the accuracy of the semi-empirical model.