Fourth-order Runge-Kutta integration with stepsize control

The rest of the arguments are standard and so omitted. This completes the proof . The prototype AMCD spacecraft was found to be asymptotically stable where the parameters used are: Ia = 680 kgm , / f l , = 1360kg-m 2 , / 5 =680kg-m 2 , / 5 Z =453.3kg-m 2 , # = 0.76 m, a =0.76 m, wap=401,3 rad/sec, o^0 = 0.1 rad/sec, ^ = 1020, A^=2856. Simulation was reported for larger k^, k^, where the system was found stable. A considerable amount of work is needed for selection of the best parameters. Further simulation is needed when one or more ball-in-tube dampers are present. Note that smaller damper masses appear to stabilize the system.