冲量法测试固体推进剂高压动态燃速及压强指数
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摘要
为了解决固体推进剂在高压下燃速测试方法的不足,提出了一种固体推进剂高压动态燃速测试方法———冲量燃速测试法。该方法通过固体推进剂在火箭发动机中的增面燃烧,得到发动机工作过程中的递增F—t曲线和p—t曲线,根据单位时间产生的冲量与已燃烧推进剂质量的关系(冲量法),计算得到了发动机工作全过程中不同时刻对应压强下的燃速值。实验对比了在助推器中常规双铅-2(SQ-2)推进剂的燃速与冲量法测得的燃速,并通过测试某中能推进剂的燃速对冲量燃速测试法进行验证。结果表明,冲量法测得SQ-2推进剂在压强为10.62、7.89和7.63M Pa下的燃速分别为12.134、11.369和11.258mm/s;而助推器法在相应压强下的燃速分别为12.056、11.104和10.91mm/s,冲量法所得结果略高,最大误差约为3%;冲量法测得某中能复合推进剂的燃速特性为r=6.46p~(0.443)(p=8～23M Pa)、r=3.49p~(0.635)(p=23～47MPa);实现了通过单次增压实验测试固体推进剂任意压强点的燃速。
In order to solve the deficiency of the testing method of burning rate of solid propellant under high pressures, a high-pressure dynamic burning rate test method for solid propellant, impulse burning rate test method, was proposed. In this m ethod, the increm ental F-t curve and p-t curve during the mo tor working process were obtained by increasing surface combustion of solid propellant in the rocket motor. According to the relationship between the impulse generated per unit time and the mass of burned propellant(impulse method), the burning rate values under the corresponding pressure at different time during the whole working process of the motor were calculated and obtained. The burning rate of the conventional propellant SQ-2 in booster was experimentally compared with that measured by impulse method, and the impulse burning rate test method was verified by testing the burning rate of a medium-energy propellant. The results showthat the burning rates of pro pellant SQ-2 measured by im pulse method are 12.134 m m/s at 10.62 MPa, 11.369 mm/s at 7.87 MPa and11.258 mm/s at 7.63 MPa, while tho se measured by booster method are 12.056, 11. 104 and 10.91 mm/s under the corresponding pressure. The results obtained by impulse method are slightly higher, with a maximum error of about 3%. The burning rate characteristics of a medium-energy compo site propellant measured by impulse method are r=6.46 p0.443(p=8-23 MPa), r=3.49 p0.635(p=23-47 MPa). The measurement of burning rate at any pressure point of the solid propellant is realized by a single pressurization experiment.
In order to solve the deficiency of the testing method of burning rate of solid propellant under high pressures, a high-pressure dynamic burning rate test method for solid propellant, impulse burning rate test method, was proposed. In this m ethod, the increm ental F-t curve and p-t curve during the mo tor working process were obtained by increasing surface combustion of solid propellant in the rocket motor. According to the relationship between the impulse generated per unit time and the mass of burned propellant(impulse method), the burning rate values under the corresponding pressure at different time during the whole working process of the motor were calculated and obtained. The burning rate of the conventional propellant SQ-2 in booster was experimentally compared with that measured by impulse method, and the impulse burning rate test method was verified by testing the burning rate of a medium-energy propellant. The results showthat the burning rates of pro pellant SQ-2 measured by im pulse method are 12.134 m m/s at 10.62 MPa, 11.369 mm/s at 7.87 MPa and11.258 mm/s at 7.63 MPa, while tho se measured by booster method are 12.056, 11. 104 and 10.91 mm/s under the corresponding pressure. The results obtained by impulse method are slightly higher, with a maximum error of about 3%. The burning rate characteristics of a medium-energy compo site propellant measured by impulse method are r=6.46 p0.443(p=8-23 MPa), r=3.49 p0.635(p=23-47 MPa). The measurement of burning rate at any pressure point of the solid propellant is realized by a single pressurization experiment.
引文
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[2]Gupta G,Jawale L,Mehilal,et al.Various methods for the determination of the burning rates of solid propellants-an overview[J].C entral 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]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.PEI Q ing,Z HAO Feng-qi,LU O Yang,at al.R esearch progress of burning rate measurement technology for solid propellants[J].C hinese Journal of Explosives&Propellants(Huozhayao Xuebao),2015,38(3):9-14.
[5]张小平,李葆萱,汪越,等.NEPE推进剂的高压燃烧特性研究[J].推进技术,2008,29(4):508-512.Z HAN G Xiao-ping,LI Bao-xuan,WAN G Yue,et al.Study on high pressure combustion characteristics of N EPE propellant[J].Journal of Propulsion Technology,2008,29(4):508-512.
[6]Zhao Na,Cao Y,Dai W,et al.Combustion experiment of the high bore pressure propellant under high pressure and optimization model of burning rate[C]∥29th International Symposium on Ballistics.Beijing:International Bauistics C ommittee,2016,1(2):661-675.
[7]JB770B-2005,方法706.1.燃速-靶线法和.706.2.燃速-水下声发射法[S].北京:国防科学技术工业委员会,2005.
[8]GJB770B-2005,方法705.2.比冲-推力台法[S].北京:国防科学技术工业委员会,2005.
[9]胡松启,李葆萱,李逢春,等.密闭燃烧器法测高压下推进剂燃速研究[J].含能材料,2005,13(3):189-191.HU Song-qi,LI Bao-xuan,LI Feng-chun,at al.C losed burning method for measuring burning rate of propellant under high pressure[J].C hinese Journal of Energetic Material,2005,13(3):189-191.
[10]温刚,堵平,廖昕.用密闭爆发器测定发射药实际燃速的原理和方法[J].火炸药学报,2011,34(3):57-60.WEN Gang,D U Ping,LIAO Xin.Principles and methods of measuring the actual burning rate of propellants by closed bomb[J].C hinese Journal of Explosives&Propellants(Huozhayao Xuebao),2011,34(3):57-60.
[11]刘科祥,赵露,李博.密闭自升压式固体推进剂动态燃速的测试方法[J].火炸药学报,2014,37(1):78-81.LIU Ke-xiang,Z HAO Lu,LI Bo.Test method for dynamic burning rate of closed self pressurized solid propellants[J].C hinese Journal of Explosives&Propellants(Huozhayao Xuebao),2014,37(1):78-81.