As　a　crucial　part　of　micro-satellite,　the　spatial　deployable　mechanism　has　the　direct　effects　on　satellite　performance　and　success　or　failure　of　flight　mission.　With　requirements　of　lightless　and　low　cost　for　satellite,　the　tape　spring　hinges　are　widely　used　for　their　simple　structural　form,　high　reliability　of　deployment,　high-driving　performance　and　accurate　positioning　in　deployable　mechanism.　Strain　energy　stored　in　the　folding　process　of　tape　spring　hinge　is　transformed　into　kinetic　energy　to　achieve　the　deployment　of　solar　panels.　When　in　full　deployment,　the　tape　spring　hinge　can　realize　self-locking　based　on　its　critical　moment.　Tape　spring　is　the　crucial　component　of　a　novel　space　deployable　structure　that　applied　to　solar　panels.　Its　full　deployment　determines　the　normal　function　of　satellite　in　space.　Mechanical　properties,　steady-state　moment　and　fatigue　life,　are　observed　in　folding　and　deploying　processes,　which　are　affected　by　geometric　parameters.　Influences　of　thickness,　subtended　angle,　radius　and　length　on　the　fatigue　life　of　tape　spring　are　carried　out　to　through　numerical　simulations　so　as　to　ensure　a　multi　folding　and　deploying　cycles　for　tape　spring　hinge.　Results　show　that　thickness　has　the　greatest　influence　on　the　fatigue　life,　subtended　angle　and　radius　are　second,　and　the　influence　of　length　on　fatigue　life　is　relatively　small.　On　the　basis,　the　optimal　model　is　established　based　on　response　surface　methodology　with　the　thickness　and　radius　as　design　variables,　steady　moment　as　constraint,　and　fatigue　life　as　optimization　objective.　By　using　genetic　algorithm　to　solve　the　model,　optimal　design　is　obtained　within　the　constraint,　and　then　the　optimal　design　is　remodeled　and　simulated,　and　the　obtained　results　indicate　the　accuracy　of　the　optimal　design.　This　research　could　be　a　reference　for　the　stability　design　of　space　deployable　structures.　©　Published　under　licence　by　IOP　Publishing　Ltd.