摘要
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.
| 源语言 | 英语 |
|---|---|
| 页(从-至) | 998-1000 |
| 页数 | 3 |
| 期刊 | Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics |
| 卷 | 29 |
| 期 | 11 |
| 出版状态 | 已出版 - 11月 2003 |
指纹
探究 'Servo-elasticity test of an aircraft with the flight control system' 的科研主题。它们共同构成独一无二的指纹。引用此
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