US 12,486,049 B2
Display apparatus and method for monitoring the structural integrity of a repair location
Thomas Körwien, Taufkirchen (DE); Anton Maier, Taufkirchen (DE); Thomas Kruse, Hamburg (DE); and Jens Holtmannspötter, Erding (DE)
Assigned to Airbus Defence and Space GmbH, Taufkirchen (DE)
Appl. No. 17/296,398
Filed by Airbus Defence and Space GmbH, Taufkirchen (DE)
PCT Filed Nov. 25, 2019, PCT No. PCT/EP2019/082450
§ 371(c)(1), (2) Date May 24, 2021,
PCT Pub. No. WO2020/109242, PCT Pub. Date Jun. 4, 2020.
Claims priority of application No. 102018129872.2 (DE), filed on Nov. 27, 2018.
Prior Publication US 2022/0033106 A1, Feb. 3, 2022
Int. Cl. B64F 5/40 (2017.01); B29C 65/82 (2006.01); B29C 73/10 (2006.01); B29C 73/24 (2006.01); B64F 5/00 (2017.01); B64F 5/60 (2017.01); G01N 19/04 (2006.01)
CPC B64F 5/40 (2017.01) [B29C 73/10 (2013.01); B29C 73/24 (2013.01); B64F 5/00 (2013.01); B64F 5/60 (2017.01); G01N 19/04 (2013.01); B29C 65/8207 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An indication device for monitoring a structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin,
wherein the indication device has at least one elongate, thin indicator strip detachably applied to an outer layer of the laminate structure in an immediate vicinity of the repair location; and
wherein the indicator strip is configured to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material,
wherein the indicator strip has a predefined prestress matched to a target strength to be achieved of the adhesive joint of the repair patch to surrounding composite material, and
wherein the indicator strip is applied to the cured adhesive joint by an adhesive.