On requirements for attitude dynamics and stability control for tethered satellite systems

In the recent years the use of the space shuttle technology leads to numerous new concepts of space missions and structures. A group of them are the experiments with Tethered Satellite Systems (TSS) consisting of two subsatellites (the shuttle itself and a probe for example). Such flights can be designed for various purposes like the exploration of the upper portion of the atmosphere for planets like Earth, Mars etc., which is impossible with other equipment. When the orbit eccenticity is zero the stationary position of the TSS (its number and location) is determined by distance between the subsatellites l. This paper investigates how attitude dynamics can be controlled for eccentric orbits with a simple feedback of the pitch angle in form l = l(J). The method is partly analytic based on Lagrangian formulation of the equation of motion, nonlinear analysis and nonlinear oscillation theory. Numerical simulations are also performed to study the effect of the control and justify the results.