Guidance strategy for low-thrust transfer trajectories based on optimal states feedback technology

The guidance algorithm for spacecraft is one of the difficult techniques in low-thrust transfer research. In this paper, we have presented an autonomous guidance strategy based on optimal states feedback technology. First, by utilizing classical Gauss motion equations, we derived the three separate control laws, which could maximize the time rate of change of a desired orbital element. Then, the separate control laws were blended based on the deficit between current and target value of orbital state. Finally, to obtain the optimal guidance law effectively and reliably, a hybrid method combining genetic algorithm with sequential quadratic programming was used to optimize the weight values. The guidance law design is simple, without relying on a stored reference trajectory, and could be used for spacecraft's autonomous guidance. Furthermore, it has the characteristic of near optimal-fuel. The effectiveness of the guidance algorithm has been validated by numerical simulation.