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Pneumatic-Based Approach for Flight Control
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AI
DOI：10.2514/1.c038755.png)
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Abstract
En 中文
A new flight control system using pneumatic actuation has been developed. The device is located under the skin of the upper wing surface, positioned between the maximum airfoil thickness and the trailing edge and extending over portions of the wing span. This device is activated to facilitate airplane maneuvers, such as turning, high-lift operations, or spoiler deployment. The effector is connected to a high-pressure air source and incorporates discrete nozzles that produce two families of blowing jets, which can either streamline the flow to augment lift or disturb the flow to reduce lift. The nozzles are selectively actuated to generate the required forces and moments for the desired maneuver. The parameters characterizing this flight control technique for the selected airplane maneuver are systematically analyzed through computational simulations. The effectiveness of this actuation method is demonstrated for two different aircraft configurations. A set of alternative actuation layouts is described. Additionally, ejectors that can generate a variety of actuation patterns are also presented. This dual-mode actuation approach decouples local lift and drag to mitigate adverse yaw during coordinated turn entry, reducing rudder demand, and actuator power requirements compared with conventional control surfaces.
Keywords:
ACTIVE FLOW-CONTROL
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