燃气混合火箭性能计算及试验研究  

Performance Prediction and Test Investigation of Gas-hybrid-rocket

作　　者：马聪慧[1] 曹军伟[1] 崔金平[1] 刘爱华[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2011年第5期129-131,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：以最小吉布斯自由能法为基础开发了适用于燃气混合火箭的性能预测代码,进行了60个工况的性能计算,计算结果表明,若采用含硼富燃料和85%过氧化氢为推进剂,在5MPa燃烧室压力下,燃气混合火箭比冲可以达到2600N.s/kg。在理论研究基础上,研制了燃气混合火箭原理样机,成功地进行了地面点火试验。燃气混合火箭原理样机工作正常,燃烧效率达95%。通过调节氧化剂流量,燃气混合火箭推力调节比达到5∶1,试验实测数据与性能预测结果吻合良好。A performance predictive code for gas-hybrid-rocket has been developed based on the minimum Gibbs free energy method.A group of performance parameters of gas-hybrid-rocket which use boron fuel-rich propellant and 85% H2O2 were presented by this code.According to the calculation results,the specific impulse of gas-hybrid-rocket achieved 2600N·s/kg while the combustor＇s pressure was 5MPa.The model machine was designed and manufactured based on the theoretical investigation,the ground ignition test of model machine was successfully conducted in Oct.2009,the model machine operated steadily with 95% combustion efficiency and 5∶1 thrust adjust ratio due to adjustment of oxidant flow-rate.

关 键 词：燃气混合火箭 性能预测 地面点火试验 推力调节 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]