Systems and methods to prevent cracking of exterior paint along structural joints of painted aerospace components

• US 10,449,725 B2
• Filed: 12/14/2016
• Issued: 10/22/2019
• Est. Priority Date: 12/14/2016
• Status: Active Grant

• Current Assignee: Embraer S.A.
• Original Assignee: Embraer S.A.
• Inventors: Weber, Fabio Angheben, Vasquez De Mesquita, Cleber, Gouvea, Felipe Henrique, Alexandre De Barros Mendes, Paulo
• Primary Examiner(s): Thomas, Alexander S
• Application Number:
  US15/378,520
• Publication Number:
  US 20180162513A1
• Time in Patent Office: 1,042 Days
• CPC Class Codes: B29C 65/48 using adhesives , i.e. using supplementary joining material; solvent bonding
• CPC Class Codes: B64C 1/069 Joining arrangements therefor
• CPC Class Codes: B64F 5/00 Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
• CPC Class Codes: F16J 15/02 between relatively-stationary surfaces F16J15/46, F16J15/48 take precedence
• CPC Class Codes: Y10T 428/197 with noncoplanar reinforcement

Abstract

Anti-paint cracking systems are provided as part of a painted aerospace component (e.g., a fuselage, an engine nacelle, a wing, an empennage, a fairing and the like) having a pair of adjacent structural panels defining therebetween a joint space having a lengthwise extent and a finished paint topcoat covering an exterior surface of the adjacent structural panels and the joint space therebetween. The anti-paint cracking system will thus be associated with the joint space along the lengthwise extent thereof and positioned below the finished paint topcoat. The anti-paint cracking system will include a joint sealant positioned in the joint space and an adhesive tape or a fibrous tape formed of a fiber composite material applied over the joint space and the joint sealant positioned therein.

Claims

1. A method to prevent crack formation along a lengthwise extent of a joint space between painted exterior surfaces of adjacent metal structural panels of an aerospace component, wherein the method comprises:

(a) providing adjacent metal structural panels of an aerospace component which abut one another along opposed non-recessed edges so as to define a non-recessed joint space therebetween, wherein the adjacent metal structural panels are connected to one another at interior surfaces thereof by a splice plate and a series of fasteners connecting the metal structural panels to the splice plate and spaced-apart relative to the joint space so as to define a region therebetween which includes the joint space, wherein the splice plate extends along the lengthwise extent of the joint space to close the joint space at the interior surfaces;

(b) filing the joint space with a joint sealant;

(c) applying a primer coating onto at least a portion of the exterior surfaces of the adjacent metal structural panels so as to cover the sealant filling the joint space and the portion of the exterior surfaces of the adjacent metal structural panels adjacent to the joint space;

(d) applying a fibrous tape comprised of synthetic fibers embedded in a curable polymeric matrix onto the applied primer coating on the exterior surfaces of the adjacent metal structural panels adjacent to the joint space within the region defined between the series of fasteners so that the fibrous tape covers the sealant filling the joint space between the adjacent structural panels and is positioned over adjacent regions of the exterior surfaces of the structural panels but does not cover the series of fasteners;

(e) allowing the polymeric matrix to cure;

(f) applying a secondary primer overcoat onto at least the fibrous tape such that the secondary primer coating extends over and beyond lateral edges of the fibrous tape to thereby cover the fibrous tape; and

thereafter

(g) applying a paint topcoat layer over the secondary primer coating covering the fibrous tape and the exterior surfaces of the adjacent structural panels.

2. The method as in claim 1, wherein step (d) is practiced by orienting the synthetic fibers in the fibrous tape at an angle of about 45°

relative to the lengthwise extent of the joint space.

3. The method as in claim 1, wherein the fiber composite material comprises synthetic fibers embedded in a polymeric adhesive matrix.

4. The method as in claim 3, wherein the synthetic fibers are selected from the group consisting of glass fibers, carbon fibers, boron fibers, aramid fibers and mixtures thereof.

5. The method component as in claim 4, wherein the polymeric adhesive matrix comprises an epoxy resin.

6. The method as in claim 5, wherein step (d) includes orienting the synthetic fibers in the fibrous tape at an angle of about 45°

relative to the lengthwise extent of the joint space between the adjacent panels.