Research On Method And Policy Of Large Scale Orbital Maneuver Of Spacecraft

This paper mainly discuss the problem of method and policy of spacecraft's large scale orbital maneuver. The basis of dynamics and simulation includes the iterative flyout angle algorithm to the solutions to Lambert Problem and Battin's universal conic section state extrapolate method. Then spacecraft's orbit roots, maneuver impulse and maneuver time are discussed as the following four part:First of all, the chaser's one orbit roots is selected as a variable to simulate its influence to the large scale orbital maneuver. The research reveals fact that the orbit roots both of chaser and target should be close to each other to achieve better maneuver and rendezvous' ability, moreover, the best orbit maneuver and rendezvous occurs when both chaser and target's initial phase angle are equal.Then, the chaser's two orbit roots are selected as variable and visualizing the simulation by contour plot. This part of research draws the conclusion the same as the first part when the target's orbit is circular orbit, while the selected two variable can be wildly changed if the target's orbit is elliptical orbit.Next, wait time before orbit maneuver is simulated. The analysis shows that the wait time and maneuver impulse have close relationship to target's orbital period. If the time waited properly, the maneuver impulse can be greatly reduced.Finally, this paper tried to start a new research field that named as Rendezvous Area and Space Control Body, by introducing these concept, visualization for large scale orbital maneuver was able to show directly.In the end, this paper presents final conclusion and make expectation for the future research work.