US 12,448,151 B2
Method for producing a perforated nacelle inlet assembly
Charles William Rust, Seattle, WA (US); John Alfred Weidler, III, Lynnwood, WA (US); and Martin Wood, Newcastle Upon Tyne (GB)
Assigned to The Boeing Company, Arlington, VA (US); and CAV Advanced Technologies LTD, Consett (GB)
Filed by THE BOEING COMPANY, Arlington, VA (US); and CAV ADVANCED TECHNOLOGIES LTD., Consett (GB)
Filed on Jul. 17, 2024, as Appl. No. 18/775,577.
Application 18/775,577 is a division of application No. 18/165,714, filed on Feb. 7, 2023, granted, now 12,077,320.
Claims priority of provisional application 63/368,560, filed on Jul. 15, 2022.
Prior Publication US 2024/0367819 A1, Nov. 7, 2024
Int. Cl. B64F 5/10 (2017.01); B23K 26/382 (2014.01); B64D 15/06 (2006.01); B64D 29/00 (2006.01)
CPC B64F 5/10 (2017.01) [B23K 26/382 (2015.10); B64D 15/06 (2013.01); B64D 29/00 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A perforation forming system comprising:
a laser device;
a memory storage device that stores a set of instructions that are computer-readable; and
a control unit operably connected to the laser device and the memory storage device, wherein the control unit executes the set of instructions to control the laser device to laser drill a plurality of perforations through an entire thickness of a lipskin at different locations within a perforation zone of the lipskin so that a percent open area of the perforation zone is less than 2%, wherein the lipskin has a curved contour and includes a metallic coating that defines an exterior surface of the lipskin and a composite panel that defines an interior surface of the lipskin, wherein the laser device is controlled by the control unit to emit laser beams that impinge upon the interior surface of the lipskin and penetrate the composite panel before penetrating through the metallic coating.