| 摘要 |
A wing load alleviation system (10) and method for alleviating the lift-inducing structural-bending force (i.e., moment) experienced by each of the wings (12) of an aircraft (14). The apparatus includes a deployable panel and an actuator mounted in each wing. The actuators are responsive to a command generator (15B). The actuator is mounted inside the wing and the panel is mounted flush with an outer surface of its respective wing. Each panel can be moved between a retracted position, where it has no affect on airflow moving over the wing, to a deployed position in which it deflects air off of the wing. Each panel is preferably located at a span-wise location at least about halfway along the length of the wing toward the wing tip (16), and more preferably at least in part outboardly of the outboard-most trailing edge device (42) in the wing. The apparatus effectively shifts the lift-inducing structural-bending forces experienced by the wing more inboard towards the fuselage. |
