Satellite Solar Panel Deployment Mechanism

Resettable solar array deployment mechanism.

Satellite solar panel deployment mechanism.

A test bed for the solar panel deployment testing has been developed supporting the solar array during deployment reproducing the dynamical situation in orbit. 1 an active hinge which provides the kinetic energy of deployment by two redundant torsional springs 2 a passive hinge which controls the rotational speed by means of a brushed dc motor and undergoes locking in the intended position when the solar panel deployment phase finishes. Consequently the analysis on the dynamic characteristic of the deployment mechanism must be done at an initial design stage. Solar array panels of a satellite must be locked at an intended position in order to perform its mission successfully as the electric power source of a satellite.

To deploy the solar panels completely it is necessary to design the deployment mechanism which has high precision and reliability. Solar array structures and mechanisms deployment. Deployed concentrators around solar panel. The computer aided design cad files and all associated content posted to this website are created uploaded managed and owned by third party users.

The mechanism is designed around the concept of deploying a solid strut using counter rotating cylinders joined by a cable. Self actuated deployment mechanisms utilized the stored energy in a torsion spring to drive the solar arrays during the unfolding phase after orbital insertion. Composite structures large flexible array panels solar cells and thin lightweight. Esa has developed a deployment and locking mechanism that fits within the frame surrounding a standard solar panel.

The deployment system is based on a plastic fiber wire and thermal cutters guaranteeing a suitable level of reliability. Kevin vipavetz vip senior systems engineer. To deploy the solar panels. The solar panel deployment mechanism includes two parts see fig.

Satellite solar panel deployment demonstrator. In such cases the motion has to be controlled by drag braking to reduce or eliminate the shock loading at the end of the stroke. Solar array panels of a satellite must be locked at an intended position in order to perform its mission successfully as the electric power source of a satellite.