In this study a novel aircraft trailing edge flap actuation system was developed and tested. Pneumatic artificial muscles (PAMs) were used as the driving elements of this system to demonstrate their feasibility and utility as an alternative aerospace actuation technology. A prototype flap/actuator system was integrated into a model wing section and tested on the bench-top under simulated airloads for flight at 100ms~(-1) (M = 0.3) and in an open-jet wind tunnel at free stream velocities ranging up to 45ms~(-1) (M = 0.13). Testing was performed for actuator pressures ranging from 0.069 to 0.62MPa (10-90 psi) and actuation frequencies from 0.1 to 31Hz. Results show that the PAM-driven trailing edge flap system can generate substantial and sustainable dynamic deflections, thereby proving the feasibility of using pneumatic artificial muscle actuators in a trailing edge flap system. Key issues limiting system performance are identified, that should be resolved in future research.
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