摘要
自行设计、研制了实验室尺度的N2O/HTPB(端羟基聚丁二烯)混合火箭发动机的原理样机,并进行系列试验。分析实时的试验数据,获得了HTPB退移速率方程,以及发动机推力、比冲等性能参数。建立了可模拟发动机工作和性能的仿真模型。发动机主要工作参数的模拟结果和试验数据吻合较好,误差不超过3%。计算结果显示氧化剂与燃料质量比随时间的变化受制于退移速率方程中的系数n,对于N2O/HTPB这种推进剂组合,氧化剂与燃料质量比将随时间降低。对发动机性能的分析评估表明,低氧化剂与燃料质量比对发动机性能影响显著,故有必要增加N2O的流量。
A lab-scale N2O/HTPB （hydroxyl-terminated polybutadiene） hybrid rocket motor prototype was designed, built and tested. The real-time experimental data was analyzed to obtain the regression rate equation for the HTPB, the motor＇s thrust and the specific impulse performance. A computer model was then developed to simulate the motor＇s operation and performance. Computational and experimental results for the motor＇s operational parameters are in good agreement with errors of less than 3%. The results indicate that the oxidant/fuel mass ratio （to/F） as a function of time depends on the coefficient n in the regression rate equation and decreases with time for the N2O/HTPB propellant combination. The analysis of the motor＇s performance suggests that it suffers greatly from low rO/F and the N2O flow rate needs to be increased.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2008年第2期285-288,共4页
Journal of Tsinghua University(Science and Technology)
基金
国家教育振兴计划(514200620405)
关键词
混合火箭发动机
N2O
HTPB
燃料退移速率
航天推进
hybrid rocker motor
N2O
HTPB （hydroxyl terminated polybutadiene）
fuel regression rate
space propulsion
