Today, numerous aeroelastic structures are deployed over a finite time period, such as flaps, spoilers, control surfaces, and wheel bay and bomb bay doors. These devices must be both divergence and flutter free. Current state-of-art simulations verify this by applying a quasi-steady assumption that does not require the system to physically deploy within the computations. That is, the structure is assumed elastic but does not possess the “large” motion associated with the device’s path of travel. While these simulations have strong technical merit, especially in the case where a structure is inadvertently locked in a partially deployed position, they are unable to capture all of the relevant physics.
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