Geometric characterization and rapid computation method for reachable domain of spacecraft with single impulse

The reachable domain is an effective means for multi-objective selection and sequence optimization in future multi objective rendezvous missions, such as on-orbit servicing and space debris removal. A representation and efficient calculation method for the envelope of fixed-time reachable domain by geometric features is proposed to address the issues in time sensitivity and heavy computational burden in traditional numerical methods for calculating fixed-time reachable domain. Firstly, based on the Monte Carlo simulation results, the sensitivity of the characteristic parameters of reachable domain envelope to maneuver parameters is analyzed. Then, based on the conclusion of sensitivity analysis, a new method for characterizing the reachable domain envelope of spacecraft with single impulse by geometric features was proposed. Finally, a deep neural network was introduced to establish a mapping relationship between maneuvering parameters and geometric characteristic parameters of envelope, which addresses the inherent contradiction between the computational efficiency and accuracy of existing numerical methods and realizes rapid and high-precision calculation for fixed-time reachable domain of spacecraft with single impulse. The simulation results show that the reachable domain calculated by proposed method matches well with the Monte Carlo simulation results and significantly improves computational efficiency.