Aircraft wing with sequentially-timed bellows assembly for optimizing boundary layer control
View Patent ↗Methods for optimizing Boundary Layer Control (BLC) systems and related systems (e.g. a Laminar Flow Control (LFC) system or systems, a Static Pressure Thrust (SPT) system or systems, a Boundary Layer Ingestion (BLI)/Wake Immersed Propulsion (WIP) system or systems, and/or low-dissipation BLC fluid-movement system or systems) to operate in concert with each other and a bellows air-moving system are disclosed.
1. An aircraft wing with a system for optimizing boundary layer control, comprising:
an enclosing structure having a leading edge, a trailing edge, a first wing portion extending between the leading edge and the trailing edge, and a second wing portion extending between the leading edge and the trailing edge and disposed opposite the first wing portion;
an inner cavity defined within the enclosing structure;
at least one bellows assembly disposed in the inner cavity and including at least one primary bellows and at least one secondary bellows operating in a sequentially-timed manner with the primary bellows;
wherein the at least one bellows assembly is spaced apart from inner surfaces of the leading edge, the trailing edge, the first wing portion, and the second wing portion so as to define a void between the at least one bellows assembly and the inner surfaces;
a first boundary control inlet defined in the first wing portion and in communication with the void; and
a second boundary control inlet defined in the second wing portion and in communication with the void.
2. The aircraft wing of claim 1 , further comprising at least one further boundary control inlet defined in the first wing portion and in communication with the void.
3. The aircraft wing of claim 1 , further comprising a series of boundary control inlets defined in the first wing portion and in communication with the void.
4. The aircraft wing of claim 2 , wherein the at least one further boundary control inlet is arranged rearwardly of the first boundary control inlet and aligned, in a chordwise direction of the wing, with the first boundary control inlet.
5. The aircraft wing of claim 3 , wherein the series of boundary control inlets is arranged rearwardly of the first boundary control inlet and aligned, in a chordwise direction of the wing, with the first boundary control inlet; and
wherein the boundary control inlets of the series of boundary control inlets are arranged in a front-aft direction of the wing and aligned in the chordwise direction of the wing.