Basing on the background of operationally responsive satellites in practical missions, the orbital design method is researched in this paper. First, combing with the relation of launch point and objective point position, the inequality relation between the orbital altitude and the operationally responsive time is established, involving the constraints of the operationally responsive time. Then, according to the spherical triangle theory, the equations of orbital inclination and RAAN are established. Furthermore, aiming at an assumed object region, two different types of operationally responsive orbit with different responsive times are simulated in STK. Also, the feasibility has been verified.