The invention provides a total temperature and total pressure measurement method for a high-Mach-number aircraft, and the method comprises the steps: building a corresponding relation between wall surface pressure and total pressure through innovative molded surface design and structural design; obtaining a theoretical incoming flow total enthalpy and a theoretical incoming flow total temperature based on a sound velocity flow relationship; the theoretical incoming flow total enthalpy and the theoretical incoming flow total temperature are corrected by simulating a high-speed incoming flow environment in an arc wind tunnel. Based on the understanding of a high-Mach-number flow field mechanism, a high-Mach-number total temperature real-time measurement scheme is formed by solving the problem that the total pressure under the flight condition is difficult to integrally measure, and the method can be suitable for total temperature and total pressure measurement of a high-Mach-number aircraft.
本发明提供了一种用于高马赫数飞行器的总温总压测量方法,通过创新型面设计、结构设计、建立壁面压力与总压的对应关系;基于声速流动关系获取理论来流总焓和理论来流总温;通过在电弧风洞中,模拟高速来流环境,修正理论来流总焓和理论来流总温。本发明基于对高马赫数的流场机理认识,通过解决了飞行条件总压难以一体化测量的难题,形成高马赫数的总温实时测量方案,能够适用于高马赫数飞行器的总温总压测量。
Total temperature and total pressure measuring method for high Mach number aircraft
一种用于高马赫数飞行器的总温总压测量方法
2025-01-21
Patent
Electronic Resource
Chinese
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein |
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