Rapid-response launch missions impose stringent requirements on both mission
design timeliness and orbital insertion accuracy. However, strong coupling
exists among key node parameters such as launch window, launch azimuth, and
pitch program angles, making conventional sequential design approaches
inefficient and inadequate for rapid-response mission planning. To address this
issue, this paper proposes a rapid determination method for key node parameters
covering the entire launch process. First, an analytical launch window
determination model based on orbital geometry is established by explicitly
formulating the mathematical relationship between launch timing and the orbital
plane, enabling efficient evaluation of feasible launch opportunities. On this
basis, a parameterized trajectory modeling approach combined with a Newton
iteration method is employed to rapidly optimize the launch azimuth as well as
the first- and second-stage pitch program parameters. A closed-loop
collaborative optimization framework is then constructed to coordinate launch
parameters and trajectory parameters, in which a hierarchical strategy
consisting of coarse window screening and refined parameter optimization is
adopted to synchronously determine all key mission parameters. Finally, terminal
iterative guidance is introduced to compensate for accumulated deviations and
further improve orbital insertion accuracy. Simulation results demonstrate that
the proposed method achieves high-precision orbital insertion, with the
semi-major axis error at the meter level and the errors in eccentricity,
inclination, and right ascension of the ascending node all on the order of
10^-7. The proposed approach, therefore, provides both excellent
design efficiency and terminal accuracy for rapid-response launch missions.