论文部分内容阅读
超音速进气道设计、试验、系统匹配和制造技术的开发是此项研究工作的基础之一。试验设备现已交付使用。对单个进气道和配置进气道的测试能力进行了充分的研究。研究了一种带放气口的进气道方案，并可用于整体式火箭冲压发动机飞行试验导弹。研究工作涉及进气道设计过程、风洞性能试验、系统匹配、制造、飞行试验数据采集和分析。目前，重点放在研究工作上，致力于各姿态角和超额定马赫数下性能的研究。
The development of supersonic inlet design, testing, system matching and manufacturing technology is one of the foundations of this research. Test equipment is now delivered. A thorough study of the test capabilities of a single inlet and an inlet is provided. A kind of air intake with vent was studied and it can be used in monolithic rocket ramjet flight test missile. Research involves the intake port design process, wind tunnel performance testing, system matching, manufacturing, flight test data acquisition and analysis. At present, emphasis is placed on research work dedicated to the study of the performance under various attitude angles and over-rated Mach number.