Air vehicle capturing, connecting and separating device

Abstract

The invention discloses an air vehicle capturing, connecting and separating device. The air vehicle capturing, connecting and separating device comprises an active unit and a passive unit. The active unit comprises a shell, a motor, a sliding lead screw and at least two capturing claws. The motor drives the sliding lead screw to rotate so that reverse motion of a nut and the capturing claws can be achieved. The passive unit comprises a passive part, a guiding rod and a pressing plate. The guiding rod is connected between the passive part and the pressing plate. The pressing plate slides on the guiding rod. Through the electric-driven hinged capturing claws, capturing, connecting and separating of air vehicles are achieved, and the air vehicle capturing, connecting and separating device has the advantages of being large in capturing range, simple in mechanism structure, low in mass and the like.

Description

technical field [0001] The invention relates to a capture, connection and separation device, in particular to a docking device which can be used for small aircrafts. Background technique [0002] At present, in the existing small-scale docking devices for spacecraft, the capture mechanism mostly adopts the claw mechanism, and the opening angle of the claw mechanism generally does not exceed 180°. Therefore, it is difficult for the existing docking device to achieve large-scale capture; Most of them are in the form of multi-links, and the mechanism configuration is relatively complicated. In addition, the elastic elements that apply the pressing force between the active and passive aircraft are mostly installed on the active aircraft, which further increases the structural complexity of the active aircraft. Contents of the invention [0003] The invention provides an aircraft capture connection and separation device to solve the above-mentioned defects in the prior art and ...

AI Technical Summary

Problems solved by technology

[0002] At present, in the existing small-scale docking devices for spacecraft, the capture mechanism mostly adopts the claw mechanism, and the opening angle of the claw mechanism generally does not exceed 180°. Therefore, it is difficult for the existing docking device to achieve large-scale capture; Most of them adopt the form of multi-links, and the mechanism configuration is relatively complicated. In addition, the elastic elements that apply the pressing force between the active and passive aircraft are mostly installed on the active aircraft, which increases the structural complexity of the active aircraft.

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