翼柱形模拟发动机点火燃气填充过程研究  

Study on ignition gas-filling course of simulation test motors with fin-slot configurated grain

作　　者：赵汝岩[1] 于胜春[2] 李昊[3] 徐勇[3] 

机构地区：[1]海军航空工程学院七系,烟台264001 [2]海军航空工程学院飞行器工程系,烟台264001 [3]海军航空工程学院研究生管理大队,烟台264001

出　　处：《固体火箭技术》2009年第3期258-261,共4页Journal of Solid Rocket Technology

摘　　要：含翼槽发动机点火燃气填充过程对固体火箭发动机整个点火升压过程有着潜在影响。通过试验,测定在不同点火药量、不同堵片打开方式下,点火燃气填充过程中头部和尾部翼槽内的压强变化情况以及两翼槽内的压强响应时间间隔,并建立了模拟发动机的点火燃气填充过程计算模型,计算结果与实测数据吻合较好。结果发现,堵片的状况影响两翼槽内的压强变化情况,同时两翼槽内的压强响应时间间隔与燃烧室内主流燃气速度有关。Ignition gas-filling process in the fin-slot region is of the potential influence on the behavior of the overall ignition transient. The pressure and the time interval between the fin-slots of simulating test motor during the gas-filling process was acquired during the test. And then a calculation model of the gas-filling of simulating test motors with fin-slot eonfigurated grain was developed and the calculated results agree with the test data. The result shows that the nozzle closure situation effects the pressurization process in the fin-slots. The time interval of pressurization in the fin-slots is correlated with the initial gas velocity.

关 键 词：模拟固体火箭发动机 点火 翼槽 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]