Abstract: Aiming at the problem of precision decline caused by orbital perturbations during the descending orbit interception of thin film spacecraft, an orbital control optimization algorithm based on optimal attack and sideslip angles is proposed. Firstly, the algorithm calculates the interceptable region based on the orbital dynamics characteristics of the thin film spacecraft, then determines whether the target is within the region to narrow down the search range for the optimal orbit. Drawing inspiration from the strategy used in reentry spacecraft which controls attack and sideslip angles, the algorithm seeks to minimize the miss distance as the objective function while subject to the constraint of fixed attack angle for thin film spacecraft. The particle swarm algorithm is employed to find the optimal solution for the attack angle. Lastly, to mitigate the effects of non-spherical Earth perturbations, a slight adjustment to the normal direction of interception orbit is achieved by introducing sideslip angles, thus enhancing the interception probability. Simulation demonstrate the thin film spacecraft can intercept the co-planar targets in low earth orbit with good terminal accuracy under both ideal gravitational filed and non-spheriacl perturbation gravitational filed. The work can provide a new idea for the removal and mitigation of space junk, and also has a certain reference significance for the development of new low-cost orbital interception.

Key words:  thin film spacecraft, descending orbit interception, attack and sideslip angles, interceptable region, miss distance