Research on Ascent Phase Guidance Technology Based on Uncertainty Parameter Online Identification

In response to the challenges of numerous constraints in the ascent phase of composite-powered carriers, narrow flight corridors, and poor adaptability of guidance to deviations in aerodynamic coefficients, atmospheric density, and thrust, this paper proposes an ascent guidance method based on online identification of uncertain parameters. An online identification model based on acceleration information is established to identify the magnitude of parameter deviations. Trajectory profiles matching the magnitude of parameter deviations are selected online from a trajectory database to ensure that the guided vehicle reaches the starting window of the next mission within the constraints under deviation conditions. Simulation results demonstrate that this method enables rapid online selection of a trajectory adapted to the current composite uncertainties, thereby enhancing the robustness of ascent phase guidance schemes for composite-powered carriers.