Development and demonstration of a flutter-suppression system using active controls

The application of active control technology to suppress flutter was demonstrated successfully in the transonic dynamics tunnel with a delta-wing model. The model was a simplified version of a proposed supersonic transport wing design. An active flutter suppression method based on an aerodynamic energy criterion was verified by using three different control laws. The first two control laws utilized both leading-edge and trailing-edge active control surfaces, whereas the third control law required only a single trailing-edge active control surface. At a Mach number of 0.9 the experimental results demonstrated increases in the flutter dynamic pressure from 12.5 percent to 30 percent with active controls. Analytical methods were developed to predict both open-loop and closed-loop stability, and the results agreed reasonably well with the experimental results.

[1]  E. Nissim,et al.  Recent advances in aerodynamic energy concept for flutter suppression and gust alleviation using active controls , 1977 .

[2]  K. G. Pratt,et al.  A survey of active controls benefits to supersonic transports , 1976 .

[3]  David L. Gray,et al.  Transonic Study of Active Flutter Suppression Based on an Energy Concept , 1975 .

[4]  D. B. Debra,et al.  Control law synthesis and sensor design for active flutter suppression. , 1973 .

[5]  Gerald E. Bergmann,et al.  Design and Evaluation of Miniature Control Surface Actuation Systems for Aeroelastic Models , 1973 .

[6]  H. A. Cole,et al.  On-line failure detection and damping measurement of aerospace structures by random decrement signatures , 1973 .

[7]  R. V. Hood,et al.  Active controls - Changing the rules of structural design. , 1972 .

[8]  William E. Triplett,et al.  A Feasibility Study of Active Wing/Store Flutter Control , 1972 .

[9]  Glenn O. Thompson,et al.  Active Flutter Suppression - An Emerging Technology , 1972 .

[10]  E. Nissim,et al.  Flutter suppression using active controls based on the concept of aerodynamic energy , 1971 .

[11]  J. I. Arnold,et al.  Flight test evaluation of an advanced stability augmentation system for B-52 aircraft. , 1969 .

[12]  W. Rodden,et al.  A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows. , 1969 .

[13]  K. L. Roger,et al.  Evaluation of B-52 structural response to random turbulence with stability augmentation systems. , 1967 .

[14]  R. Swaim,et al.  Controlling dynamic response in rough air , 1966 .

[15]  R. A. Pepping.  A Theoretical Investigation of the Oscillating Control Surface Frequency Response Technique of Flight Flutter Testing , 1954 .

[16]  Charles C. Kennedy,et al.  Use of Vectors in Vibration Measurement and Analysis , 1947 .

[17]  L. J. Topp,et al.  Potential performance gains by use of a flutter suppression system , 1971 .

[18]  Robert P. Johannes,et al.  Active flutter control??Flight test system synthesis , 1971 .

[19]  E. Naumann,et al.  A noncontacting displacement measuring technique and its application to current vibration testing , 1966 .

[20]  A. G. Rainey,et al.  On the prediction of critical flutter conditions from subcritical response data and some related wind tunnel experience , 1958 .