Service HotlineThe cylindrical pin magnetic positioning automatic press-in mechanism includes a base, a guide block is arranged on the base, one end of the guide block is provided with a guide vertical plate, and a push-up column is arranged under the end, and the push-up column is connected with a driving mechanism to drive The mechanism is arranged inside the guide vertical plate; one side of the guide block is provided with a push plate, the end of the push plate is provided with a semicircular groove, the push plate is connected to the driving mechanism, and the driving mechanism is arranged on the base The other side of the guide block is provided with a workbench located on the base, an error-proof positioning mechanism is arranged above the workbench, a press-in mechanism is arranged above the error-proof positioning mechanism, and one side of the error-proof positioning mechanism is provided. There is an error-proof detection mechanism; the press-in mechanism includes a punch, a punch block and an upper template arranged in sequence from bottom to top, and the upper template is driven and connected with five driving mechanisms; the error-proof detection mechanism includes a fixed angle plate, a fixed angle The plate is arranged on the worktable, and the fixed angle plate is provided with a four-drive mechanism, and the four-drive mechanism is connected to the detection head.
Due to its convenient operation, quick-release screws are widely used in aviation recording equipment, such as the operation panel on the central console of the aircraft, the upper operation panel, etc. However, the assembly of quick-release screws needs to be assembled in sequence. Springs and quick-release screw rods, usually the quick-release screw crimping tools provided by external suppliers can only crimp some small-sized quick-release screws, or custom-made quick-release screw crimping tools for a certain product, time and cost are very high, so it is necessary to design a quick-release screw assembly device for general aviation airborne equipment.
2. Low cycle fatigue Low cycle fatigue means that the fatigue stress is close to or exceeds the yield limit of the material. The material has a certain amount of plastic deformation in each strain cycle. The life is generally in the range of 102 to several times 104, and the fatigue curve is generally used. ε-N curve representation. The finite element calculation results show that after the bolt is screwed into the lock nut, the stress at the root of the threaded piece is large, and part of the surface area is in a yield state, while the strain in the central area of the root of the threaded piece is small, and the strain situation is more complicated. The area with high strain at the root of the thread piece experiences reciprocating loading, which is prone to low cycle fatigue, which reduces the pressure of the thread piece and reduces the screw-out torque.
At present, most of the thread locking structures use an integral nut and a matching external thread screw structure. To remove the nut from the screw rod, it must be completely unscrewed along the screw rod, which is time-consuming and labor-intensive. It is more inconvenient to install.
In the design of modern aviation and aerospace vehicles, in order to reduce weight and save space, the space of the fastening installation system is getting narrower and narrower, and blind hole installation is often required. In this case, single-sided riveting installation is usually used for fastening connection. At present, this kind of fastening connection products are mainly blind rivets. The riveting installation principle of blind rivets is to use the method of pulling, pulling the mandrel, and extruding the nail sleeve to deform it at the blind end to achieve the function of fastened connection. This kind of fastening connection method requires special riveting, generally imported riveting, the replacement of internal parts is expensive, the installation process is complicated, and the installation cost is high.
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