摘要
以一架具有飞行控制系统的飞机为对象 ,开展了伺服弹性 (结构模态耦合 )试验研究 ,旨在揭示该飞机的伺服弹性稳定性本质 .同时 ,阐述了结构模态耦合试验的方法和原理 ,给出了典型状态的试验结果 ,并与计算分析结果进行了比较 .
In order to reveal the servo-elasticity stability nature of an aircraft equipped with a flight control system, some active-control-system/structural dynamics interaction tests have been performed. The test principle and test method were described. Some typical test results were presented and compared with the calculated results, showing that the test method is reasonable.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第11期998-1000,共3页
Journal of Beijing University of Aeronautics and Astronautics
关键词
伺服系统
试验
稳定性
Control systems
Elasticity testing
Servers
Stability
Structure (composition)
