This research investigates the feasibility of using Pneumatic Artificial Muscles (PAMs) to drive a rotor blade Trailing Edge Flap (TEF) for primary control and/or vibration reduction. Specifically, this work investigates the effects of operating these compliant, pneumatic actuators under the high CF loading typical of a helicopter rotor blade. A prototype TEF actuation system was designed and built. It was tested in a vacuum whirl chamber over a range of centrifugal accelerations. Bi-directional actuation was performed to track changes in system performance with increasing CF field. Additionally, testing was performed under different levels of torsional spring loading to simulate aerodynamic hinge moment effects. Results of these tests motivated a second experiment wherein the effects of CF loading on the PAMs themselves are isolated from the rest of the system. This was accomplished by fixing the ends of PAM and performing blocked force testing over a range of centrifugal accelerations. Taken together, these tests show that chordwise PAM actuators are capable of operating under high CF loading with only minor losses in performance. Additionally, the need for careful design of actuation and flap system components for operation in this harsh environment is reiterated.
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