微爆轰推力器的冲量研究  

Calculation for the Impulse of Micro-Detonation Thruster

作　　者：郭香华[1] 董良慈[2] 何远航[1] 张庆明[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081 [2]中国三江航天集团设计所,湖北武汉430035

出　　处：《北京理工大学学报》2008年第5期377-380,共4页Transactions of Beijing Institute of Technology

基　　金：国家“八六三”计划项目(70107003)

摘　　要：利用瞬时爆轰假设以及小药量线性近似,假设推力单元内的微量含能材料的爆轰反应在瞬时完成,从理论上计算了微爆轰推力单元在真空中的冲量和推力,并在此基础上研究了含能材料的爆热、产物的等熵指数以及喷管的长度对单元的冲量和推力的影响,并通过数值模拟得到喷管底部压力曲线及单元冲量随喷管药柱长度比的变化.结果表明,推力单元的冲量随装药质量、等熵指数和比爆热的增大而增加;为了获得理想的推进性能,喷管的长度不能小于装药长度的4倍.Using the instantaneous detonation assumption and linear approximation of tiny charge mass,the impulse and thrust of a micro-detonation thrust unit operating in vacuum are theoretically calculated.Based on this,the influences of specific detonation heat,isentropic exponent and length of the nozzle on the impulse and the thrust are studied.Furthermore,by numerical simulation,the time-dependence of the pressure on the end of nozzle is obtained,and the variation of impulse provided by the micro-thruster with the length ratio of nozzle to energetic material is also investigated.The results showed that increasing the charge mass,the isentropic exponent and the specific detonation heat can enhance the impulse of a thrust unit,and the nozzle length must be over 4 times of the charge length to achieve the perfect propulsion performance.

关 键 词：微推力器 爆轰 冲量 含能材料 喷管 

分 类 号：O383.3[理学—流体力学]