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US 11,142,296 B2Granted
Apparatus for laminar flow control
AssigneeAirbus Operations GmbH
InventorsVernon Holmes, Rodney Evans
Life of this patent
Estimating the term…
Abstract
Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.
Claims19
A joint strap for controlling laminar flow over a skin of an aircraft, the joint strap configured to be received into a recess of the skin to join a first skin panel to a second skin panel, the joint strap comprising:
- a body defining a chamber, and the body comprising:
- an outer portion configured to align with an outer surface of the skin panel when the body is received in the recess, the outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures in fluid communication with the chamber;
- and
- a support portion configured to support outer portion, the support portion defining at least one outlet from the chamber for air drawn from the chamber by suction through the outlet,
- wherein the joint strap is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use;
- wherein the chamber is between a base portion and the outer portion,
- wherein the support portion comprises the base portion and at least one support member,
- wherein the at least one support members extends from the base portion and through the chamber to support the outer portion;
- wherein the body comprises at least one fastener receiving portion configured to receive a respective fastener to fasten the body to the first skin panel or the second skin panel, and -each of the at least one fastener receiving portion comprises a respective one of the at least one support members.
6 more elements
A system for laminar flow control for an aircraft, the system comprising:
- a first skin panel comprising a first recess and a first edge adjacent the first recess;
- a second skin panel comprising a second recess, wherein the second skin panel includes a second edge adjacent both the second recess and the first edge;
- a joint strap seated in the first and second recesses and spanning between the first and second skin panels, the joint strap including:
- an outer portion having an outer surface aligned with outer surfaces of the first and second skin panels, wherein the outer portion includes micro apertures open to the outer surface of the outer portion and open to an interior chamber of the joint strap;
- a support portion supporting the outer portion, wherein the support portion includes a base portion opposite the outer portion, and support members within the interior chamber, wherein the support members span between the base portion and the outer portion;
- a fastener receiving aperture in each of a plurality of the support members;
- a fastener in each of the fastener receiving apertures, wherein each fastener secures the base portion to the first skin panel or the second skin panel;
- and
- an outlet in the support portion and configured to be coupled to a suction source, wherein air is drawn through the micro-apertures, into the interior chamber and through the outlet by the suction source.
6 more elements
A laminar flow control apparatus comprising:
- a joint strap configured to cover a gap between a first skin panel and a second skin panel of an aircraft, wherein the joint strap includes:
- an internal cavity;
- an outer portion including micro apertures providing fluid communication between the internal cavity and an outer surface of the joint strap, wherein the outer surface is aligned with an outer surface of the first and an outer surface of the second skin panel;
- a support portion including a base portion opposite the outer portion, wherein the internal cavity is between the base portion and the outer portion,
- support members spanning between the base portion and the outer portion, and the support members are within the internal cavity,
- a fastener receiving aperture in each of a plurality of the support members;
- fasteners each in a respective one of the fastener receiving apertures, wherein a first fastener of the fasteners secures the joint strap to the first skin panel and a second fastener of the fasteners secures the joint strap to the second skin panel;
- and
- at least one outlet extending through the base portion, in fluid communication with the internal cavity, and configured to be connected to a suction source;
- wherein, the suction source, while connected to the at least one outlet, draws air from the internal cavity causing air to be drawn in to the internal cavity from the exterior of the joint strap via the at least one micro aperture.
7 more elements
A skin panel assembly for an aerodynamic structure of an aircraft, the skin panel assembly including:
- a first skin panel including a first outer surface, a first recess in the first outer surface, and a first edge adjacent the first recess;
- a second skin panel including a second outer surface, a second recess in the second outer surface, and a second edge adjacent the second recess and adjacent the first recess of the first skin panel;
- a joint strap spanning a gap between the first and second edges of the first and second skin panels, wherein the joint strap is seated in the first and second recesses and the joint strap includes:
- a third outer skin surface aligned with the first and second outer surfaces;
- micro-apertures in the third outer skin surface;
- an internal chamber within the joint strap, wherein the micro-apertures are in fluid communication with the internal chamber, wherein the internal chamber overlaps at least partially the first and second recesses;
- a base portion opposite to the third outer skin surface, wherein the internal chamber is between the base portion and the third outer skin surface,
- support members spanning between the base portion and the third outer skin surface, wherein the support members are within the internal chamber,
- a fastener receiving aperture in each of a plurality of the support members,
- fasteners each in a respective one of the fastener receiving apertures, wherein a first fastener of the fasteners secures the joint strap to the first skin panel and a second fastener of or the fasteners secures the joint strap to the second skin panel, and
- an outlet port in fluid communication with the internal chamber and connectable to a suction source.
8 more elements
Dependencies are inferred from the claim text.