A system for applying a web around a cylindrical object with even tension containing a core having a generally cylindrical shape and a pair of handles. Each handle has an insertion area, a collar area, and a gripping area. The collar area is sandwiched between the insertion area and the gripping area and the insertion diameter is less than the inner diameter of the core at the first end and second end. The handles and core have a means for coupling meaning that the core and the insertion area of the handles do not move independently from one another.

A system for applying a web around a cylindrical object with even tension containing a core having a generally cylindrical shape and a pair of handles. Each handle has an insertion area, a collar area, and a gripping area. The collar area is sandwiched between the insertion area and the gripping area and the insertion diameter is less than the inner diameter of the core at the first end and second end. The handles and core have a means for coupling meaning that the core and the insertion area of the handles do not move independently from one another.

To reduce a time required for repairing a honeycomb core sandwich panel. A repair method according to the present invention is a repair method, in which a repair patch 20 is disposed on a repair target portion that exists on the side of a repair surface 1A of a honeycomb core sandwich panel 1, the honeycomb core sandwich panel 1 being formed by sandwiching a honeycomb structured core 10 with a plurality of cells between skins 11 and 12, the method including: a heating step of heating the repair patch 20; and a cooling step of cooling the honeycomb core sandwich panel 1 from the side of a second surface 1B opposing the repair surface 1A of the honeycomb core sandwich panel 1.

To reduce a time required for repairing a honeycomb core sandwich panel. A repair method according to the present invention is a repair method, in which a repair patch 20 is disposed on a repair target portion that exists on the side of a repair surface 1A of a honeycomb core sandwich panel 1, the honeycomb core sandwich panel 1 being formed by sandwiching a honeycomb structured core 10 with a plurality of cells between skins 11 and 12, the method including: a heating step of heating the repair patch 20; and a cooling step of cooling the honeycomb core sandwich panel 1 from the side of a second surface 1B opposing the repair surface 1A of the honeycomb core sandwich panel 1.

The present invention sufficiently heats a repairing material while preventing change in quality of a base material provided with the repairing material so as to securely bond the repairing material to a repair target portion. The repair method of the present invention, in order to repair a repair target portion 14 existing in an outer panel 1, includes: a repairing material disposing step of disposing a repairing patch 21 including a resistance heating element 23 and a carbon fiber reinforced resin, and an adhesive 22A including a thermosetting resin before being hardened for bonding the repairing patch 21 on the repair target portion 14; and a heating-hardening step of heating and hardening the thermosetting resin of the adhesive 22A by causing the resistance heating element 23 to generate heat through supply of electricity thereto.

An in-situ double vacuum debulk (DVD) composite repair system designed to produce partially or fully cured autoclave-quality hot-bond composite repairs on contoured structures. The system provides vacuum pressure for hot bond repairs to be performed on flat and contoured structures using one set-up capable of debulking (partially curing) and then fully curing composite repairs on composite and metallic aircraft structures. The use of in-situ DVD also eliminates handling of the patch/adhesive when transferring from an off-aircraft DVD chamber to the repair site on the aircraft. This can increase the probability of successful repairs because the possibility of contaminating and misaligning the adhesive and repair patch are eliminated.

An in-situ double vacuum debulk (DVD) composite repair system designed to produce partially or fully cured autoclave-quality hot-bond composite repairs on contoured structures. The system provides vacuum pressure for hot bond repairs to be performed on flat and contoured structures using one set-up capable of debulking (partially curing) and then fully curing composite repairs on composite and metallic aircraft structures. The use of in-situ DVD also eliminates handling of the patch/adhesive when transferring from an off-aircraft DVD chamber to the repair site on the aircraft. This can increase the probability of successful repairs because the possibility of contaminating and misaligning the adhesive and repair patch are eliminated.

A method of repairing a first automotive part that includes providing a connector tab and applying a fluidic thermoplastic material to the connector tab and/or the first automotive part to attach the connector tab to the first automotive part. The connector tab comprises: a retainer portion sized to attach to the first automotive part, wherein the retainer portion has a plurality of holes formed therethrough, and wherein the plurality of holes is configured to receive the fluidic thermoplastic material to secure the retainer portion to the first automotive part; and a coupler portion defining a shape corresponding to a portion of the first automotive part, the coupler portion forming a coupler, which is configured to operably engage another coupler of a second automotive part.

A method of repairing a first automotive part that includes providing a connector tab and applying a fluidic thermoplastic material to the connector tab and/or the first automotive part to attach the connector tab to the first automotive part. The connector tab comprises: a retainer portion sized to attach to the first automotive part, wherein the retainer portion has a plurality of holes formed therethrough, and wherein the plurality of holes is configured to receive the fluidic thermoplastic material to secure the retainer portion to the first automotive part; and a coupler portion defining a shape corresponding to a portion of the first automotive part, the coupler portion forming a coupler, which is configured to operably engage another coupler of a second automotive part.

This automaton for applying a patch to a draping surface (15) comprises a gripper (24) capable of grasping the patch and depositing it on the draping surface (15), and a heating system (25) for directly heating the draping surface (15).