摘要
通过对某型飞机进气系统工作原理和特性的分析,深入研究了进气道喘振的故障机理,有针对性地制定了规避措施,飞行试验结果表明：在定性分析及定量分析基础上制定更加合理的调节规律,增加补充调节规律,规范试飞员大马赫数大迎角的试飞方法通过上述措施有效解决了故障,飞行安全得到大大地提升,对排除进发匹配故障提供了参考和借鉴。
The working principle and characteristics of an aircraft inlet system are analyzed, and failure mechanism of the inlet surge is deeply studied, and specific evasive measures are formulated. The flight test results show that based on qualitative analysis and quantitative analysis, a more reasonable adjustment rule is formulated, the supplementary regulation rule is increased, the flight test method with high Mach number and large angle of attack is standardized. The above measures have effectively solved the fault and greatly improved the safety of the pilot, which provides a reference for eliminating the inletengine matching fault.
作者
于海涛
徐伟
臧旭
YU Hai-tao;XU Wei;ZHANG Xu(PLA Military Representative Of？ee in Shenyang Aireraft Industry（Group）Co.,Ltd.,Shenyang 110850,China)
出处
《测控技术》
CSCD
2018年第B09期269-271,276,共4页
Measurement & Control Technology
关键词
进气道
紊流
调节斜板
MA
控制规律
inlet
turbulence
adjustable inclined plate
Ma
control law
