虚拟技术在固体冲压发动机地面试验系统中的应用  

The application of virtual technology in solid ducted rocket ground test system

作　　者：李进贤[1] 岳春国[1] 侯晓[1] 冯喜平[1] 唐金兰[1] 

机构地区：[1]西北工业大学航天学院

出　　处：《实验技术与管理》2009年第1期78-81,94,共5页Experimental Technology and Management

基　　金：国防重点实验室基金试点项目(51470020604HK1401)

摘　　要：在深入分析固体火箭冲压发动机试验系统的组成和参数特点的基础上，提出了发动机温度、压力、流量及其推力测量的总体方案和进气模拟总体控制方案。利用LabVIEW测量与自动化软件开发平台，开发了适用固体火箭冲压发动机试验推力、压力、流量和温度测量的数据采集软件。基于PID控制器开发了温度、压力调节控制软件，能根据试验要求自动地调节空气和燃油的流量，能实现进气温度、压力模拟和试验过程控制。开发了通用的温度、压力、流量、推力等物理量标定程序，并建立了相应的试验数据库。Based on the parameter characteristics of the engine thermodynamics and the air-inlet simulation, the measurement and control schemes are designed with virtual instrument technology. The experimental data acquisition software, which can acquire temperature, pressure, flow rate, and thrust of the engine, is developed by LabVIEW software development platform. With PID, air inlet simulation control software is programmed at the same time, which can control the total temperature and pressure of the air-inlet efficiently. In addition, the parameter calibration of the engine and the experiment database are accomplished.

关 键 词：国体火箭冲压发动机 参数测量 试验控制 虚拟仪器 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]