固体火箭发动机点火试验测试系统设计  

Design of Solid Rocket Motor Ignition Test System

作　　者：姜明[1] 毛露[1] 于殿泓[1] 

机构地区：[1]西安理工大学机械与精密仪器工程学院,西安市710048

出　　处：《仪器仪表标准化与计量》2009年第1期10-11,14,共3页Instrument Standardization & Metrology

摘　　要：介绍了固体火箭发动机点火试验中流场测试参数的特点,并分析了对测试系统的要求,提出了采用虚拟仪器构成方式中的PXI总线进行系统设计,实现系统的同步测试和扫描测试要求。其测量数据可信,测量精度高。同时该套虚拟仪器流场综合测试系统中的采集数据能够自动处理,自动存储,具有用户接口界面友好,操作方便扩展灵活,软件维护方便等特点。The paper introduced the setup of measurement system for flow field in solid rocket motors ignition test. The design is based on PXI system which is one of the structures of virtual instrument, and the data in the measurement system is reliable as well as high measuring accuracy. Besides, the collecting data in the virtual instrument integrated test system for flow field can be automatically treated and saved. The system with the characteristics such as the userinterface is friendly, easy to operate, extand flexibly and its software maintenance conveniently.

关 键 词：虚拟仪器 总线 流场 测试 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]