固液火箭发动机试验瞬时燃速分析方法  

Instantaneous Fuel Regression Rate Analysis of Hybrid Rocket Motor Experiment

作　　者：李新田[1] 曾鹏[1] 田辉[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2012年第2期211-215,共5页Journal of Propulsion Technology

摘　　要：介绍了一种用于固液火箭发动机试验的瞬时燃速分析方法,运用该方法对H2O2/HTPB固液火箭发动机单室双推力长时间热试车试验进行燃速分析,拟合得到该工况下的燃速公式为r=1.847×10-2G0o.7304。根据燃速公式等计算结果对一次发动机试验进行了预估,计算得到的预估内弹道性能曲线与试验结果吻合较好,验证了该瞬时燃速分析方法的可行性,为发动机工作时间较长、氧化剂流率变化较大时的燃速分析提供了一种途径。This paper proposes an instantaneous fuel regression rate analysis method for hybrid rocket motor experiment when the oxidizer mass flux changes large during a long working time. The method is applied on a single-chamber dual-thrust hybrid rocket long-time test with the hydrogen peroxide（H2O2） and hydroxyl-terminated polybutadiene（HTPB） propellant combination, and the fuel regression rate formula,r = 1. 847 × 10 2 Go ^0.7304 , is fitted based on the analysis results. According to the fitted fuel regression rate formula and calculation results, the prediction performances of a test are produced. The results show that the prediction interior ballistics performances fit well with the test curves, which validates the feasibility of the analy- sis method.

关 键 词：固液火箭发动机 瞬时燃速 地面试验 内弹道 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]