Add to ORKGThe design of the flutter suppression system for a remotely-piloted research vehicle is described. The modeling of the aeroelastic system, the methodology used to synthesized the control law, the analytical results used to evaluate the control law performance, and ground testing of the flutter suppression system onboard the aircraft are discussed. The major emphasis is on the use of optimal control techniques employed during the synthesis of the control law
Mathematical models to be used in the control system design were developed. A computer program, whic...
Three flutter suppression control law design techniques are presented. Each uses multiple control su...
Testing and evaluation of a stability augmentation system for aircraft flight control were performed...
A control law is developed to suppress symmetric flutter for a mathematical model of an aeroelastic ...
The final design and hardware fabrication was completed for an active control system capable of the ...
Three control law design techniques for flutter suppression are presented. Each technique uses multi...
A study to develop analytical procedures to be used in the checkout and calibration of a flutter win...
The synthesis, implementation, and wind tunnel test of two flutter suppression control laws for an a...
Flight flutter-test results of the first aeroelastic research wing (ARW-1) of NASA's drones for aero...
The use of eigenspace techniques for the design of an active flutter suppression system for a hypoth...
Eigenspace (ES) techniques were used to design an active flutter suppression system for the DAST ARW...
The synthesis and experimental validation of a control law for13; an actiqe flutter suppression syst...
Results of work done on active controls on the modified YF-17 flutter model are summarized. The basi...
Two flutter suppression control laws were synthesized, implemented, and tested on a low speed aeroel...
The Active Flexible Wing Project is a collaborative effort between the NASA Langley Research Center ...
Mathematical models to be used in the control system design were developed. A computer program, whic...
Three flutter suppression control law design techniques are presented. Each uses multiple control su...
Testing and evaluation of a stability augmentation system for aircraft flight control were performed...
A control law is developed to suppress symmetric flutter for a mathematical model of an aeroelastic ...
The final design and hardware fabrication was completed for an active control system capable of the ...
Three control law design techniques for flutter suppression are presented. Each technique uses multi...
A study to develop analytical procedures to be used in the checkout and calibration of a flutter win...
The synthesis, implementation, and wind tunnel test of two flutter suppression control laws for an a...
Flight flutter-test results of the first aeroelastic research wing (ARW-1) of NASA's drones for aero...
The use of eigenspace techniques for the design of an active flutter suppression system for a hypoth...
Eigenspace (ES) techniques were used to design an active flutter suppression system for the DAST ARW...
The synthesis and experimental validation of a control law for13; an actiqe flutter suppression syst...
Results of work done on active controls on the modified YF-17 flutter model are summarized. The basi...
Two flutter suppression control laws were synthesized, implemented, and tested on a low speed aeroel...
The Active Flexible Wing Project is a collaborative effort between the NASA Langley Research Center ...
Mathematical models to be used in the control system design were developed. A computer program, whic...
Three flutter suppression control law design techniques are presented. Each uses multiple control su...
Testing and evaluation of a stability augmentation system for aircraft flight control were performed...