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Volume 29 Issue 11
Nov.  2003
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Journal of Beijing University of Aeronautics and Astronautics  > 2003  >  29(11): 998-1000.
Zhang Junjie, Yang Chao. Servo-elasticity test of an aircraft with the flight control system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11): 998-1000. (in Chinese)
Citation: Zhang Junjie, Yang Chao. Servo-elasticity test of an aircraft with the flight control system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11): 998-1000. (in Chinese)
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Servo-elasticity test of an aircraft with the flight control system

  • School of Aeronautics Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 05 Jul 2003
  • Publish Date: 30 Nov 2003
    Abstract
  • To discover the servo-elasticity stability nature of an aircraft equipped with a flight control system, some active-control-system/structural dynamics interaction tests on it have been performed. The test principle and test method was described. Some typical test results have been presented and compared with the calculated results. The test method is reasonable.

     

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    • References(1)
  • [1] Taylor R, Roger W P, Brian D C. The application of actuator performance limits to aeroservoelastic compensation . AIAA-95-1195-CP, 1995 [2] Peloubet R P. YF-16 active-control system/structural dynamics interaction instabilily . AIAA 75-823, 1975 [3] 管 德. 飞机气动弹性力学手册[M]. 北京:航空工业出版社, 1994.195~205 Guan De. Aeroelasticity manual[M]. Beijing:Aviation Industrial Press, 1994. 195~205(in Chinese)
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