Integrated design of sun-synchronous orbit and launch vehicle trajectory for operationally responsive space

Abstract For the operationally responsive space mission with the known launch point and target area, based on the simplified trajectory, the design method of the sun-synchronous orbit is given by the orbit dynamics, considering the mutually constrained relationship between the satellite orbit and the launch vehicle trajectory. Then, with the orbit parameters as the input, the trajectory model obtains the actual trajectory parameters. Considering the error between the actual and simplified trajectory parameters, the actual trajectory parameters are used to correct the simplified trajectory. Finally, by iterative calculation, the parameters of sun-synchronous orbit and launch vehicle trajectory for operationally responsive space are obtained with the finite trajectory error. For a typical example, the parameters are calculated by the method, which is verified by the STK simulation, demonstrating the feasibility and practicability of the method. The design method can provide theoretical support for the orbit and trajectory design of operationally responsive space.