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The present invention provides a split prevention method of stitches and a split preventor of the same. According to the invention, a wire hook is configured at the back side of a needle dropping position. The wire hook swings at a state that a curved needle enters after sewing. A hook part at the front end of the wire hook is next to the back side of the curved needle for keeping a needle wire ring in a plurality of needle wire rings, which is captured by the curved needle and is provided at an inlet side. According to the invention, the sewing of at least one needle amount is performed at this state so the needle which descends to the needle wire ring that is kept by the needle hook passes through. The needle wire which is kept by the needle is used for performing self-connection for the needle wire rings, and breaking-off of the bending needle wire is prevented through pressing the bending needle wire by a self-connection part. The split which is specific in the stitches of the double-wire whipstitch can be effectively prevented.

The invention discloses an unmanned aerial vehicle wing changing mechanism with two wings capable of changing sweepback angles synchronously and coaxially in the same plane and belongs to the technical field of unmanned aerial vehicle structural design. The unmanned aerial vehicle wing changing mechanism comprises an upper supporting board, a lower supporting board, a rotary haft, a right wing support, a left wing support, a spring, a protruding block, a limiting hook, a rack A and a rack B. The rotary shaft is connected with the lower supporting board, the left wing support, the right wing support and the upper supporting board from bottom to top. The spring is arranged between the left wing support and the lower supporting board. The rotary shaft is sleeved with the spring. By the adoption of the unmanned aerial vehicle wing changing mechanism, wings of an unmanned aerial vehicle can be folded to be stored, the storage space is reduced, and the wings can be barreled; the wings can be rapidly unfolded in the launching stage of the unmanned aerial vehicle, lift force can be established rapidly, and the situation that the height of the unmanned aerial vehicle is reduced, and even the unmanned aerial vehicle crashes can be effectively prevented; the two wings of the unmanned aerial vehicle are changed synchronously and coaxially all the time, the two wings are located on the same plane rapidly after the unmanned aerial vehicle is launched, the interference yawing moment in the transverse lateral direction can be reduced as much as possible, and control is convenient.