基于LabVIEW和组合式气路的燃速测试压强控制系统  

Pressure control system of burning rate instrument based on LabVIEW and composite gas circuit

作　　者：刘科祥[1] 赵波[2] 杨介印 陈鑫[1] 赵露[1] LIU Kexiang;ZHAO Bo;YANG Jieyin;CHEN Xin;ZHAO Lu(Xidian University,Xi'an 710126,China;Xi'an North Huian Chemical Industries Co.,Ltd,Xi'an 710302,China)

机构地区：[1]西安电子科技大学,西安710126 [2]西安北方惠安化学工业有限公司,西安710302

出　　处：《固体火箭技术》2020年第2期222-228,共7页Journal of Solid Rocket Technology

摘　　要：在固体推进剂的靶线法燃速测试中,燃烧室的压强波动直接影响数据的可信度,常用的抑制波动的方法是并联燃烧室或者缓冲机构。然而,这一方法在低压范围及气态产物量大的高燃速推进剂燃烧试验环境下,有失效的可能。为将燃速测试的压强波动稳定在国军标规定的1%范围内,分析了推进剂燃烧过程中压强波动的机理,设计了一套基于Lab?VIEW虚拟仪器和组合式气路的压强控制系统,配合现有缓冲式燃速仪,进行了1 MPa和2 MPa低压试验验证,当燃烧导致的压力上升超过国军标规定的1%时,PID控制算法开启泄压阀门,使压强回归到正常范围,整个燃烧过程的压强超标时间从原78%降至15%以内。结果表明,设计的压强控制系统,相比单纯依赖缓冲瓶,能更有效地将燃烧压强波动控制在国军标要求范围内,从而使数据更可信。Pressure plays an important role in the burning rate test of solid propellant,and the pressure fluctuation of chamber directly affects the reliability of test data.To keep the ambient pressure constant in combustion process,a buffer bottle was usually connected to the chamber in parallel.However,for some test cases,such as the burning rate test of solid propellant with low initial pressure,more gaseous products and high burning rate,the pressure fluctuation may still exceed 1%,which is not up to standard GJB 770B—2005/706.1.The mechanism of pressure fluctuation during propellant combustion was analyzed and a new testing method was introduced in the paper,based on the existing buffer air circuit structure,LabVIEW PID control algorithm and combined air circuit group were added.For tests with very low initial pressures,such as 1 MPa and 2 MPa,when the pressure caused by combustion rises by 1%,the PID control algorithm opens the exhaust valve to reduce the pressure to the normal range,and the overpressure time of the whole combustion process decreases from 78%to less than 15%.The results show that,the designed pressure control system can control combustion pressure fluctuation more effectively,and make the test data more credible than the existing method which only relies on the buffer bottle.

关 键 词：固体推进剂 燃速 压强波动 组合式气路 压强控制 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]