The invention discloses an optical deorbit method for tethered
towing of
space debris and belongs to the field of
spacecraft attitude and
orbit dynamics and control. The implementation method includes: establishing a
coupling dynamics model of the in-plane
orbit of a tethered
towing system through a Lagrange method; solving the optimal fuel problem of
transfer orbit by adopting an optimization method for
orbit transfer and ensuring a wide range of optimal orbit transfer of the tethered
towing while
system stabilizing the altitude of tethered towing
system; at the end of towing, controlling thedebris by swinging and releasing to enable the debris to
gain the maximum initial velocity and fly to the farther orbit, and completing the debris removal task while reducing fuel consumption duringthe debris removal process. With the method, wide range optimal orbit transfer of the tethered towing system can be guaranteed, and meanwhile, the attitude of the tethered towing system can be kept stable to remove the
space debris stably; besides, the final swing control makes the debris fly further into the orbit, and fuel consumption during the debris removal process is reduced.