The Study Of Reachable Domain For Spacecraft Orbital Maneuver

With the development of space technology,the external space has attracted more and more attention.Now all countries are actively exploring external space resources and making reasonable use.In order to obtain more resources,it will inevitably produce space against.This requires spacecraft with a wide range of orbital maneuverability to ensure the leading position of space technology.In the stage of human exploration of space,orbital maneuvering technology is particularly important,such as on-orbit maintenance of spacecraft,rendezvous and docking,emergency rescue,formation flight,in-track filling are all applied to this technology.In addition to requiring the spacecraft to have a wide range of maneuverability,this technology must also take into account the safety distance to prevent possible misuse of the collision.The key to these tasks lies in the orbital maneuvering technique,and the reachability of orbital maneuver is the most important.Therefore,it is important to study the maneuverability of spacecraft.In this paper,the absolute reachability of the spacecraft under pulsed maneuver is obtained by numerical analysis without considering the disturbance factors.In this paper,the absolute reachability of the spacecraft under pulsed maneuver is obtained by numerical analysis without considering the disturbance factors.Then,the relative reachability of the spacecraft under the initial uncertain conditions is studied,and the influence of the initial error on the relative distance between the spacecraft is obtained,which can provide theoretical support for real-time planning of spacecraft space missions.According to the absolute reachability problem of spacecraft,the initial orbit coordinate system and its orbital coordinate system are established,the relationship between the two coordinate systems is obtained,and the function relation of the reachable area of the spacecraft is deduced,and the function is solved by gradient method to analyze the root condition.Finally,this paper give the initial value of the spacecraft pulse without limiting the flight time of the spacecraft,obtained any maneuver point,any pulse direction of the three-dimensional spacecraft absolute reachable area.The results are clear and can directly determine the range of spacecraft flight.According to the relatively reachable region of spacecraft,a nonlinear dynamic model is introduced,and the state transition matrix is described to describe the relative motion.The reference point in the relative motion is selected reasonably,which avoids the blind area of the relative reachable area,and the function expression of relative reachable region is deduced by vector relation in the end.In the simulation,take the circular orbit as a prerequisite,the relative reachability of the spacecraft under the initial uncertainty condition is obtained after numerical calculation.