火炸药学报

为了实现单次发动机试验测得多个压强条件下推进剂的燃速,提出了一种固体推进剂动态燃速测试方法——质量流率法。该法以质量流率计算公式为依据,通过处理推进剂燃烧过程中随时间递增的压强曲线,计算得到发动机工作全过程中不同时刻对应压强下的燃速值; 对比了通过质量流率法与冲量法处理得到的双铅-2(SQ-2)推进剂燃速结果; 分析了特征速度和喷管喉径变化对质量流率法燃速测试结果的影响。结果表明,两种方法得到的燃速结果随压强变化趋势完全一致; 当压强为9.945MPa时,两种方法的误差为1.06%; 当压强为22MPa时,误差为3.87%。造成质量流率法与冲量法燃速结果之间差异的主要原因为喷管喉径实际尺寸的变化。

In order to obtain the burning rate of propellant under multiple pressures in a single engine test, the dynamic burning rate test method of solid propellant-mass flow rate method is proposed. This method is based on the mass flow rate calculated formula. By processing the pressure curve which increases with time in the combustion process of propellant, the burning rates at different times corresponding to the pressure during the entire engine operation were calculated. The burning rate results of double lead-2(SQ-2)propellant by the mass flow rate method and the impulse method were compared. The effects of characteristic velocity and nozzle throat diameter changes on the burning rate rusults by the mass flow rate method were analyzed. The results show that the burning rate results obtained by the two methods are consistent with each other. When the pressure is 9.945MPa, the error is 1.06%, and when the pressure is 22MPa, the error is 3.87%. The main reason for the difference between the mass flow rate method and the impulse method is the change of nozzle throat diameter.

引言
1 实验
2 结果与讨论
3 结论

图1 推进剂药柱结构示意图<br/>Fig.1 Schematic diagram of the propellant grain structure

图1 推进剂药柱结构示意图
Fig.1 Schematic diagram of the propellant grain structure

图2 发动机结构示意图<br/>Fig.2 Schematic diagram of the engine structure

图2 发动机结构示意图
Fig.2 Schematic diagram of the engine structure

图3 推进剂燃烧过程中的p—t变化曲线<br/>Fig.3 The p—t changing curve during the combustion process of propellant

图3 推进剂燃烧过程中的p—t变化曲线
Fig.3 The p—t changing curve during the combustion process of propellant

图4 推力和压强随时间的变化曲线<br/>Fig.4 Time dependent thrust and pressure curves

图4 推力和压强随时间的变化曲线
Fig.4 Time dependent thrust and pressure curves

表1 质量流率法所得SQ-2推进剂燃速测试计算结果<br/>Table 1 Calculated results of burning rate measurement by mass flow method for SQ-2 propellant

表1 质量流率法所得SQ-2推进剂燃速测试计算结果
Table 1 Calculated results of burning rate measurement by mass flow method for SQ-2 propellant

表2 冲量法所得SQ-2推进剂燃速测试计算结果<br/>Table 2 Calculated results of burning rate measurement by impulse test for SQ-2 propellant

表2 冲量法所得SQ-2推进剂燃速测试计算结果
Table 2 Calculated results of burning rate measurement by impulse test for SQ-2 propellant

图5 两种动态燃速测试方法的结果对比<br/>Fig.5 Comparison of testing results from two dynamic burning rate test methods

图5 两种动态燃速测试方法的结果对比
Fig.5 Comparison of testing results from two dynamic burning rate test methods

表3 两种燃速测试方法结果对比<br/>Table 3 Comparison of two burning rate test methods results

表3 两种燃速测试方法结果对比
Table 3 Comparison of two burning rate test methods results

图6 SQ-2推进剂特征速度随压强的变化曲线<br/>Fig.6 Pressure dependence curve of characteristic velocity for SQ-2 propellant

图6 SQ-2推进剂特征速度随压强的变化曲线
Fig.6 Pressure dependence curve of characteristic velocity for SQ-2 propellant

[1] 王伯羲,冯增国,杨荣杰.火药燃烧理论[M].北京:北京理工大学出版社,1997.
[2]GUPTA G,JAWALE L,EHILAL M,et al.Various methods forthe determination of the burning rates of solid propellants——an overview[J].Central European Journal of Energetic Materials,2015,12(3): 593-620.
[3]彭培根,刘培谅,张仁,等.固体推进剂性能计算原理[M].长沙:国防科技大学出版社,1987.
[4]王凯,贺晓芳,沈飞,等.超声波法测试固体火箭发动机燃速[J].中国测试,2017,43(8):19-23.

China Test,

[5]裴庆,赵凤起,罗阳,等.固体推进剂燃速测试技术研究进展[J].火炸药学报,2015,38(3):9-14.

Chinese Journal of Explosives & Propellants(Huozhaoyao Xuebao),

,

(

):

-

.

[6]裴庆.固体推进剂多靶线准动态燃速测试方法与测试系统研究[D].西安:西安电子科技大学,2013.
[7]裴庆,刘科祥,赵凤起.固体推进剂多靶线准动态燃烧性能测试法:CN,201110039791.5[P].2011.
[8]OSBORN J R, BURIEK R J, PANELLAX R J. Continuous measurement of solid propellant burning rates[J].Review of Scientific Instruments, 1966, 37(1): 86-92.
[9]王英红,刘长义,薛兆瑞,等.冲量法测试固体推进剂高压动态燃速及压强指数[J].火炸药学报,2019(3):278-283.

Chinese Journal of Explosives & Propellants(Huozhaoyao Xuebao),

(

):

-

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备注

引言

1 实验

2 结果与讨论

3 结论

期刊信息

备注

引言

1 实 验

2 结果与讨论

3 结 论

期刊信息

1 实验

3 结论