Abstract: The present invention relates to a repair method using a pre-cured repairing patch, and a repaired product obtained from repairing using the repairing patch, and the present invention securely bonds a repairing patch, where an out-of-plane stiffness is required, to a repair target. In order to cover a repair target portion 23 formed in an outer panel 2 with a repairing patch 30, and bond the repairing patch 30 to a repair target, repairing plates 31, 32 that are formed of fibers and thermosetting resin, and pre-cured before repairing are used as the repairing patch 30, and a laminating step S4 of laminating the repairing plates 31, 32, and a bonding step S7 of bonding the repairing plates 31, 32 to each other are performed.

Abstract: A repair method according to the present invention is a method for repairing a honeycomb core sandwich panel 1, the method including: a repair patch disposing step S1 of disposing a repair patch 20 and an adhesive 21A on at least one of a first surface 1A and a second surface 1B of the panel 1, the first outer skin 11 being located on the first surface 1A, and the second outer skin 12 being located on the second surface 1B; a panel restraining step S3 of sandwiching the panel 1 and the repair patch 20 from both surface sides of the first surface 1A and the second surface 1B and thereby restraining the panel 1; and a heating step (thermal curing step) S4 of heating the adhesive 21A while the panel 1 is restrained.

Abstract: A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step S2 of removing a damaged part 11 from the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step S3 of sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step S5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S6 of evacuating in a state in which the front side is sealed.

Abstract: Two open sipes are formed at a tire circumferential direction central side of a block, and closed sipes are formed in the block at both tire circumferential direction sides of the two open sipes. The depth of the open sipes is set in a range of 50 to 70% times the depth of a first circumferential direction main groove, and the depth dimension of the closed sipe is set in a range of 105 to 140% times the depth dimension of the open sipes. Accordingly high performance on ice is obtained while securing block rigidity.