Bilateral double-spring driving unfolding mechanism

Abstract

The invention provides a bilateral double-spring driving unfolding mechanism. The unfolding mechanism comprises moving hinges, fixed hinges, concentric shafts, volute spiral springs, spring blocks, spring outer end covers, spring inner ring fixing sleeves, spring outer ring fixing shafts, spring outer ring fixing sleeves, spring outer ring fixing sleeve pressing covers, locking hooks, locking hook rotating shafts, locking hook locating sleeves, locking hook locating torsional springs, locking hook locating torsional spring pressing rods, limiting screws and a microswitch. The fixed hinges and the moving hinges achieve connection and a relative rotating function through the concentric shafts, four sets of bilateral plane volute spiral springs act on the fixed hinges and the moving hinges at the same time, the locking hook locating torsional pressing rods are matched with the locking hook locating torsional springs to enable locking shafts at the tail ends of the locking hooks to slide into the bottom faces of bosses on sliding rails of the fixed hinges, so that locking locating is finished, and meanwhile the microswitch is triggered to send a successfully arriving signal to a control system. The bilateral double-spring driving unfolding mechanism is relatively simple in achievement form, achieves a driving source redundant backup function, and is light in weight, compact in structure, high in reliability and strong in bearing capacity under the same driving capacity.

Description

technical field [0001] The invention relates to a deployment mechanism, in particular to a bilateral double-spring driven deployment mechanism applied to the deployment and positioning of the mechanism in the lunar surface gravity environment and the planetary environment, and belongs to the technical field of spacecraft deployment mechanisms. Background technique [0002] The one-time action deployment mechanism usually adopts the passive drive form of the spring deployment hinge. The locking and positioning methods mainly include mechanical locking and friction self-locking. The deployment and positioning of the solar wing can be realized only by the driving torque provided by the spring on one side. However, with the continuous development of spacecraft technology, higher requirements are put forward for the driving ability and working characteristics of the deployment mechanism, and the traditional deployment mechanism driven by only one side spring can no longer meet th...

AI Technical Summary

Problems solved by technology

The use of deployment mechanisms in pairs greatly increases the weight of the system and the use of space requirements, wasting resources and space; and the assembly of multiple deployment mechanisms requires coaxial installation, which makes assembly difficult due to manufacturing errors, and is affected by the space environment during on-orbit work It is easy to produce greater deformation and partial load, and even increase the risk of locking and positioning of the deployment mechanism, reducing product reliability

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