Nominal control program for rendezvous transfer of spacecraft debris collector with electro rocket engine of low thrust at geostationary orbit

The problem of rendezvous transfer control of spacecraft debris collector, equipped with electro rocket engines of low-thrust, with fragment of space debris at geostationary orbit is studied. The problem of control program structure formation at near approach area of rendezvous transfer - spacecraft debris collector casting to safety area above fragments of space debris - is considered. The motion of spacecraft debris collector above the fragment of space debris is considered in orbital cylindrical reference frame. The secular and periodic components of relative motion gave off in implicit form. Motion control is carried out by transversal component of acceleration from thrust sign switching, radial component of acceleration is equal to zero. Boundary conditions for secular and periodic components of relative motion are formulated. The simplest structure of control program - joined control of secular and periodic components of relative motion - is studied. The base of motion control program is secular components reduction to determined state. Control program for secular components contained two active areas and passive area between them. Active area durations determined analytical as functions of boundary conditions for secular components and passive area duration (free parameter). Satisfying of boundary conditions for periodic components is carried out by passive area duration choosing and choosing of time moment correspond to first active area start moment (initial phase angle). The analytical solution for rendezvous transfer problem for chosen control program structure is formulated. The control problem reduces to non-linear trigonometric equation solving, this solution propose to determine passive area duration. Initial phase angle determine analytical by simple formula. Joined control program have limitations to boundary conditions for periodic components of relative motion. Whereupon, the rendezvous transfer strategy, takes into account limitations, is development. Numerical simulation is carried out.