| 摘要 |
FIELD: construction. ^ SUBSTANCE: device to carry out a detachable connection of structural elements, in particular, on an aircraft, comprises a clamping lever mechanism joined with the first structural element, and a clamping pin joined to the second structural element. The clamping lever mechanism comprises an eccentric shaft, a clamping lever and a driving bush. The eccentric shaft is mounted with the possibility of rotation around the rotation axis at the first structural element. The clamping lever is mounted eccentrically and with the possibility of rotation relative to the eccentric shaft. The driving bush is mounted with the possibility of rotation around the rotation axis relative to the eccentric shaft and is coupled according to the type of a geared transfer with a clamping lever. The clamping lever mechanism is arranged with the possibility of displacement between a disengagement position, an availability position and a fixing position. In the disengagement position the clamping lever and the clamping pin are disconnected, and in the fixing position the clamping lever and the clamping pin are engaged in a blocking forced manner as a result of relative rotation of the eccentric shaft and the driving bush, and also the clamping lever. The invention also relates to the method of executing a detachable connection of structural elements, in particular, on an aircraft, providing for use of the above-specified device. ^ EFFECT: safe and durable connection and high ergonomic efficiency. ^ 19 cl, 13 dwg |
