As　space　exploration　activities　are　developing　rapidly,　spacecraft　with　large　antennas　have　gained　wide　acceptance　in　providing　reliable　telecommunications　and　astrophysical　observations.　In　this　paper,　the　dynamic　responses　and　control　strategy　for　a　spacecraft　with　a　large　hoop-truss　antenna　under　solar　flux　shock　are　studied.　According　to　the　momentum　and　angular　momentum　principle,　the　rigid-flexible　coupled　rotational　dynamic　equation　and　the　translational　dynamic　equation　of　the　system　are　established,　which　include　the　attitude　motion　of　the　rigid　main　body　and　the　vibration　of　the　antenna.　Then,　a　finite　element　model　of　the　antenna　is　established　to　analytically　obtain　the　corresponding　vibration　modal　shape　matrix　and　natural　frequencies.　Last,　the　coupled　responses　for　the　attitude　motion　and　vibration　are　investigated.　The　corresponding　control　strategy　is　designed　based　on　a　double-loop　structure　sliding　mode　control　method.　The　Lyapunov　method　is　used　to　demonstrate　the　global　asymptotic　stability　of　the　system.　Simulations　verify　the　effectiveness　of　the　proposed　rigid-flexible　coupled　model　and　control　strategy.