Abstract:Aiming at the accessibility analysis for spacecraft orbit interception problem, the concepts of intercepting region and launching region for the interception spacecraft are proposed, based on the assumption of coplanar maneuver and head-on interception. Three constraints of energy, time and intersection angle are considered in the analysis. On the basis of the space reachable domain for spacecraft with single impulse, the calculating strategy of the hit region on the target orbit is established with taking the target orbit constraint into account. It is explained that the cross-over point of two non-coplanar orbits is the fuel-optimal point in the interception mission. The problems related to interception accessibility are summarized into eight basic interception problems. Through the combination of them, the calculation method of the intercepting region and launching region under the constraint of energy, time and intersection angle is described. The simulation analysis is carried out in the scene of coplanar transfer and head-on interception between two circular orbits. Simulation results show that this method can calculate the interception reachable domain for spacecraft under three constraints quickly and effectively, and can be used to analyze the interception accessibility for spacecraft in specific mission scenario.