System Vibration, Chaos and Condition Monitoring

Aerospace vehicles are subjected to complexed dynamic loads which often leads to high vibration and noise levels in flight operations. The multidisciplinary nature of aerospace structures offers many opportunities to apply innovative smart structures technologies for aircraft vibration and noise control. This presentation provides a review of smart structures research performed at the Aerospace Research Center of the National Research Council Canada for aircraft vibration and noise control applications.

The active structural acoustic control (ASAC) technology has been developed as an alternative approach to reduce the propeller aircraft cabin noise by weakening the coupling between the exterior and interior cabin acoustics. The effectiveness to reduce the cabin noise levels at the propeller blade passage frequency has been demonstrated on a full-scale Dash-8-100/200 airframe. In addition, an active noise cancellation technology has been tested on a military helicopter flight helmet to demonstrate the enhanced hearing protection to the aircrew in the laboratory.

Current aircraft high-lift devices create discontinuities and gaps in the aircraft wing airfoil shape, leading to increased drag and noise levels. A morphing wing concept that can bend and extend smoothly at the leading-edge of the wing has been developed at NRC Aerospace. The proof-of-concept morphing wing model demonstrated the ability to achieve the required high-lift airfoil shape for optimized aerodynamics in aircraft cruise and takeoff/landing conditions.

Twin-tail fighter aircraft experiences intense buffet loads when flying at high angles of attack due to vortices, which reduces fatigue life of critical structural components such as the vertical fin. In collaboration with partners from the US and Australia, several adaptive and robust control laws have been developed by NRC for the smart structures based hybrid actuation system designed for the full-scale F/A-18 aircraft vertical fin structure. The dynamic strain at the root of the vertical fin was supressed significantly through representative experiments on the F-18 vertical fin structure through a TTCP international collaboration project.

The high vibration levels inside helicopter cabin exposes the aircrew to severe whole-body vibration environment, leading to poor ride quality of the vehicle and contributing to adverse health effects to the aircrew. An active helicopter seat mount technology has been developed to reduce the vibration transmission from the helicopter floor through the seat structures to the aircrew. Extensive experiments on the active seat mount installed with a Bell-412 pilot seat and various mannequin occupants have demonstrated that the active seat mount technology was able to suppress the aircrew whole-body vibration related to the low N/rev vibration peaks, which can extend the permitted exposure time as per the ISO 2631 standard that provides health guidelines for the human whole-body vibration exposure in vehicles.