Drip-drop hovering control for mixed propulsion system

摘要

In order to satisfy the hovering technology demand for spacecraft on-orbit service task etc., based on the description method of relative orbit parameters, two parameters of semi-major axis error and eccentricity error are used for deep study of the forming of drip-drop hovering configuration in plane, and the forming condition and configuration design method are also analyzed. What's more, considering the evolution property under the electric-chemical integration propulsion system, the design method for the two parameters of in-plane hovering. Simulation results show that, the guidance scheme is correct and efficacious, the total burn-up for hovering approximates open-loop optimal performance, and the demand for engine is low, therefore it is a feasible engineering technology approach.