This　paper　proposes　a　novel　data-driven　finite-time　adaptive　control　method　for　the　spacecraft　attitude　tracking　control　problem　with　inertial　uncertainty.　Based　on　the　dynamic　regression　extension　technique,　the　disturbance　unit　matrix　is　introduced,　and　the　parameter　estimation　law　in　the　form　of　algebraic　equations　is　presented,　which　realizes　the　arbitrarily　small　convergence　of　parameter　estimation　error.　The　convergence　of　parameter　estimation　errors　is　verified　through　stability　analysis.　Globally　non-singular　fast　terminal　sliding　mode　control　is　designed　to　achieve　finite-time　arrival　of　the　sliding　surface　and　convergence　of　the　system　state　error.　The　stability　analysis　of　the　closed-loop　system　demonstrates　the　effectiveness　of　the　proposed　method.　Furthermore,　the　effectiveness　and　superiority　of　the　proposed　method　are　verified　through　numerical　simulations　of　spacecraft　attitude　tracking　control.　©　2025　COSPAR