Chinese Journal of Theoretical and Applied Mechani ›› 2016, Vol. 48 ›› Issue (1): 1-27.DOI: 10.6052/0459-1879-15-423

• Research Review •     Next Articles


Hu Haiyan, Zhao Yonghui, Huang Rui   

  1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2015-11-23 Revised:2015-11-27 Online:2016-01-18 Published:2015-12-04


The development of active control has witnessed a great change in the design of aircraft structures, from the passive design of increasing structure sti ness to the active design in view of control configured aircraft. The idea of active design does not intentionally avoid the aeroelastic problem, but adjust the structural aeroelasticity via active control so as to reduce the structure weight and optimize the aircraft performance. To achieve this purpose, it is necessary to analyze the coupling between the aircraft structure and surrounding aerodynamic loads. The aeronautical community has made great e orts to study the corresponding aeroelastic problems and gain an insight into the coupling among aircraft structure, aerodynamics and active control since 1980's. However, most studies have been based on the simplified models. As such, it is di cult to apply the research achievements to aeronautical industry. This review article surveys the recent advances in the dynamic problems of aircraft aeroelasticity including the aerodynamic nonlinearity, the backlash nonlinearity of control surfaces, instability induced by time delay in control loop, active flutter suppression, gust load alleviation, as well as corresponding wind tunnel tests. The review focuses on the new approaches proposed by the team of authors, and the corresponding numerical simulations and wind tunnel tests over the past decade. Finally, the review addresses a number of open problems related to the aeroelastic analysis and control.

Key words:

active flutter suppression|gust load alleviation|free-play nonlinearity|feedback delay|nonlinear model order reduction|wind tunnel tests

CLC Number: