Multiple Spacecraft Formation Flying Control around Artificial Equilibrium Point Using Propellantless Approach

This paper demonstrates a detailed analysis of the feasibility for compact formation system around an L2-type artificial equilibrium point by means continuous low-thrust propulsion in hybrid form solar sail and Coulomb force propulsion. Firstly, view non-ideal sail, position numerical periodic orbits L2 utilized as leader’s nominal trajectory are given. Secondly, considering external disturbances deep space environment, nonlinear dynamic model spacecraft based on circular restricted three-body problem (CRTBP) is derived, under assumption that leader covers each follower adjusts its propulsive acceleration vector (that is, both attitude electrostatic charge) order to track desired relative trajectory. Thirdly, new double power combination function reaching law, fast integral terminal sliding mode control methodology (MFITSM) ameliorated achieve orbital tracking rapidly, which has better robustness against buffeting effect during simultaneously. To properly allocate inputs, novel optimal allocation scheme designed calculate charge product spacecrafts angles, can make magnitude required from minimum avoid geometry instabilities balancing interaction between adjacent spacecraft. Finally, several examples conducted validate superiority proposed algorithm.