Dynamics and stability analysis of an orbiter-tether-maneuverable subsatellite system

Problems dealing with the dynamics and stability of the Tethered Satellite System are addressed. Nonlinear equations of motion based on a lumped-mass model are derived using a projection method. Linear equations of motion near equilibrium points are obtained via two methods, numerical and analytical linearization. For certain cases, the linear equations of motion in explicit form are used. The stability of possible equilibrium configurations of the Tethered Satellite System modeled using a point mass subsatellite is discussed in general terms. General conclusions are substantiated by specific numerical examples. Considering the end mass as a rigid body, it is shown that the rotational motion of the end body is coupled with the tether motion through the gravity gradient torque even when the attachment point is the center of mass of the end body and there are no aerodynamic forces. The results of an analysis of the motion of a Tethered Hypervelocity Vehicle are presented.