Abstract: For carrier missions on different orbits of solid rockets, the segmented ascent guidance with multiple terminal constraints is proposed based on energy management. Flight trajectory is controlled by program commands during the former segment, in which constraints can get reduced as a result of the transition from trajectory optimization to parameters optimization. Considering that increasing angleofattack can decrease velocity gain, the latter segment, the last stage of the rocket, adopts a closedloop energy management guidance to consume the redundant fuel. By alternating attitude the rocket achieves different orbits with terminal constraints of velocity, altitude and local trajectory angle. Simulation results indicate that the proposed guidance strategy shows theoretical feasibility as well as good adaptability in multiple carrier missions.