Design Of The Compliant Deployable Mechanism And Its Mechanic And Kinematic Analysis Based On Insect Mid Wings

Deployable solar arrays,the principal power-supply equipment in spacecraft,are stowed in one configuration for storage and then deployed into another configuration once in orbit in order to get lager lighting area.Based on the deployment principium of Earwig mid-wing mechanism,a new type of deployable structure of spacecraft solar arrays with single degree of freedom was designed,and such work was completed as below:1.The deployment process of Earwig mid wings was analyzed.A new kind of four-bar mechanism was obtained through the way of ‘Origami-Mechanism'.The degree of freedom of and the relationship with input and output of this four-bar mechanism was calculated.Based on that,the requirements of mechanism's complete folding,the type and moving range of driving bar and the position and number of singular points was derived.2.Based on the deployment principium of Earwig mid-wing mechanism,a new design scheme of deployable mechanisms was proposed.In order to solve the problem of position interference brought by the thickness during the process of ‘Origami-Mechanism',a stepped structure was first designed.3.Driving and locking function of tape springs was illustrated through the way of finite element analysis by ABAQUS.A new compliant hinge applied for deployable solar array was composed meeting the design requirements of tape spring compliant hinge.The new compliant hinge consisted of compliant parts(tape spring)and damping parts(shape memory alloy).4.The prototype of new deployable solar arrays was made to test the folding performance of the deployable mechanism.The driving performance,the locking performance and the deployment process of the compliant hinge was tested to verify the feasibility of the mechanism.