| 摘要: |
| 参照GJB770A-97燃烧热测试方法,采用GR3500型氧弹式热量计,实验研究了含硼贫氧推进剂燃烧热测试中存在的问题,数值模拟了氧弹中的温度分布。结果表明:含硼贫氧推进剂燃烧热测试必须解决两个主要问题:①含硼贫氧推进剂燃温高,易造成氧弹部件的烧蚀;②含硼富燃料推进剂燃烧热测试过程中,硼等难燃组分存在不完全燃烧现象。给出了解决上述问题的可行方案,实验后,氧弹部件无烧蚀;燃烧产物的分析表明,含硼贫氧推进剂在改进的氧弹式热量计中能得以完全燃烧。测试结果平行误差为1.992%。 |
| 关键词: 富油推进剂 硼化物推进剂 燃烧热 热量分析 测量设备 |
| DOI： |
| 分类号:V512 |
| 基金项目:国家博士后科学基金(2005038266) |
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| Improvement of combustion heat testing equipment of fuel-rich propellant based on boron |
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WANG Ying-hong1, DENG Yong-feng2, ZHANG Xiao-hong3, PAN Kuang-zhi1
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1.Coll.of Astronautics/National Key Lab.of Combustion,Flow and Thermo-Structure,Northwestern Polytechnical Univ.,Xi’an 710072,China;2.Coll.of Astronautics/National Key Lab.of Combustion,Flow and Thermo-Structure,Northwestern Polytechnical Univ.,Xi’an 710073,China;3.Xi’an Modern Chemistry Research Inst.,Xi’an 710065,China
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| Abstract: |
| Referring to the combustion heat testing method of GJB770A-97,with oxygen bomb calorimeter models GR3500,the problems in the combustion heat test of fuel-rich propellant based on boron were investigated.The temperature distribution trend was given by the method of numerical simulation.The results show that the combustion ablation of oxygen bomb parts and the sample incomplete combustion must be resolved in the combustion heat test for fuel-rich propellant based on boron.Feasible experimental method was put forward.The results show that the oxygen bomb parts were not ablated by combustion and the ingredient in the propellant can be burnt completely in the improved oxygen bomb.The parallel error of the test results is within 1.992%. |
| Key words: Fuel-rich propellant Boron compound propellant Heat of combustion Calorimetric analysis Measurement equipment |
