A　bistable　composite　tape-spring　(CTS)　structure　is　a　thin-walled　open　slit　tube　with　fibres　oriented　at　+/-　45　degrees,　which　is　stable　at　both　its　extended　and　coiled　configurations.　The　traditionally　manufactured　CTS　is　effectively　self-deploying.　Here,　we　devise　a　novel　manufacturing　method　to　tailor　the　deployable　mechanism　of　a　CTS.　This　is　achieved　through　adjusting　the　internal　stress　levels　by　subjecting　the　fully　coiled　as-manufactured　CTS　samples　to　additional　heat　treatment　process.　Their　deploying　performance　were　then　characterised　through　a　bespoke　axial　load　monitoring　rig,　in　order　to　reveal　the　underlying　mechanics.　It　is　demonstrated　three　different　deployable　mechanisms　can　be　manufactured　based　on　the　same　CTS,　namely　self-deploying,　neutrally　stable　and　self-coiling　CTS　structures.　The　processed　CTS　samples　also　show　specialised　stabilities,　varying　from　monostability　to　multi-stability.　The　tailoring　mechanism　is　then　proposed.　Since　the　CTS　sample　is　in　a　highly　strained　state　when　coiled,　the　polymeric　composite　material　would　slowly　deform　due　to　viscoelasticity.　According　to　the　time-temperature　superposition　principle,　the　custom　heat　treatment　of　a　fully　coiled　tape　is　equivalent　to　acceleration　of　the　viscoelastic　deformation,　where　local　stress　relaxation　occurs　on　both　the　outer　and　inner　tape　surfaces,　which　in　turn　altering　the　internal　stress　levels.　Thereby,　the　heat　treatment　processing　is　able　to　tailor　the　deployable　mechanism　of　the　CTS　structure.　These　enrich　the　deployment　diversity　of　the　CTS　to　better　fit　the　requirements　for　various　deployable　mechanisms　in　order　to　further　promote　the　applications　of　CTS　structures　to　aerospace　explorations.